N A QA E M A53 J? ,f
Copy 305
RM A53JS3
RESEARCH MEMORANDUM
THE EFFECTS OF OPERATING PROPELLERS ON THE LONGITUDINAL
CHARACTERISTICS AT HIGH SUBSONIC SPEEDS OF A FOUR-
ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 40° OF SWEEPBACK AND AN
ASPECT RATIO OF 10
By Fred B. Sutton and Fred A. Demele
Ames Aeronautical Laboratory
Moffett Field, Calif .
SlASSIFICAflO:,' NCtliD TO UICLA33I?'i32
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CLASSIFIED DOCUMENT
This material contains information affecting the National Defense of the United States within the meaning
of the espionage laws, Title 18, U.S.C., Secs. 793 and 794, the transmission or revelation of which in any
manner to an unauthorized person is prohibited by law.
NATIONAL ADVISORY COMMITTEE
FOR AERONAUTICS
WASHINGTON
January 7, 1954
CONFIDENTIAL
NACA RM A53J23
CONFIDENTIAL
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
RESEARCH MEMORANDUM
THE EFFECTS OF OPERATING PROPELLERS ON THE LONGITUDINAL
CHARACTERISTICS AT HIGH SUBSONIC SPEEDS OF A FOUR-
ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH kO° OF SWEEPBACK AND AN
ASPECT RATIO OF 10
By Fred B. Sutton and Fred A. Demele
SUMMARY
An investigation has been conducted at high subsonic speeds to
determine the effects of operating propellers on the longitudinal char-
acteristics of a four-engine tractor airplane configuration having a bO°
swept wing with an aspect ratio of 10. Wind-tunnel tests were conducted
through ranges of angles of attack and propeller thrust coefficients at
Mach numbers from 0.60 to 0.90 at Reynolds numbers of 1,000,000 and
2,000,000. The effects of varying propeller blade angle, tail incidence,
and vertical height of the horizontal tail were investigated.
The over-all effects of operating propellers on the longitudinal
characteristics were not large when compared to the effects of propeller
operation at low speed. Compared to the model with the propellers off,
operation of the propellers at constant thrust coefficients generally
decreased the static longitudinal stability. Increasing the propeller
thrust coefficient at a constant Mach number increased both the static
longitudinal stability and the trimmed lift coefficient. Operation of
the propellers at constant thrust coefficient increased the wing lift-
curve slope but had little effect on the variation of lift-curve slope
with Mach number. Operation of the propellers had little effect on the
Mach number for longitudinal force divergence at a constant lift coeffi-
cient but resulted in a decrease in the rate of change of longitudinal
force coefficient with Mach number at supercritical speeds. This effect
increased with increasing propeller thrust coefficient and with increas-
ing lift coefficient.
A method of predicting the effects of propeller normal force on the
pitching-moment characteristics of the configuration is presented. Com-
parisons with measured effects indicate that the accuracy of the method
is good.
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NACA RM A53J23
Raising the horizontal tail had little effect on the longitudinal
stability with the propellers removed but was destabilizing with the
propellers operating.
For an assumed airplane, operating at the power required for level
flight at an altitude of 40,000 feet, calculations indicate only a
small change in the stable variation of tail incidence for trim with
Mach number compared to the propellers -off condition.
INTRODUCTION
The potentialities of turbine -propeller propulsion systems are well
recognized, particularly with regard to the take-off and range capabili-
ties of multiengine airplanes. The combination of a turbine -propeller
propulsion system and an airframe configuration utilizing a sweptback
wing of high aspect ratio should make possible the achievement of long-
range flight at relatively high subsonic speeds. This propulsive system
could utilize supersonic propellers with high disc loadings. It is not
believed that the effects of these propellers on the longitudinal char-
acteristics of swept wings can be adequately predicted, either by exist-
ing theoretical methods or by available experimental data.
An investigation has been made in the Ames 12-foot pressure wind
tunnel to determine the longitudinal characteristics of a representative
multiengine airplane conf iguration with sweptback wings of high aspect
ratio. The investigation was made with and without operating supersonic
propellers. The power-off longitudinal characteristics of several com-
binations of the components of this configuration have been presented
in references 1 to 4. The characteristics of the propeller are reported
in reference 5. The results of a low-speed investigation to determine
the effects of operating propellers on the longitudinal characteristics
are presented in reference 6. The present report is concerned with the
effects of operating propellers on the longitudinal characteristics of
the configuration at high subsonic speeds. Tests were conducted over a
Mach number range of 0.60 to 0.90 at Reynolds numbers of 1,000,000 and
2,000,000. If the model is assumed to be l/l2 scale, the power condi-
tions simulated at most test Mach numbers varied from windmilling to
5000 horsepower per engine at an altitude of 1+0,000 feet or to 20,000
horsepower per engine at sea level.
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NOTATION
A a v upflow angle, average angle of local flow at the 0.7 propeller
radius and at the horizontal center line of the propeller
plane, measured with respect to the thrust axis in a plane
parallel to the plane of symmetry
a mean-line designation, fraction of chord over which the design
load is uniform
a* normal acceleration
^ wing semispan perpendicular to the plane of symmetry
b* propeller blade width
cl
C Lt
lift coefficient.
lift
qS
tail lift coefficient.
tail lift
<jS t
C m
C N
Cp
pitching -moment coefficient referred to the center of gravity,
pitching moment
qSc
(See fig. 1(a).)
propeller normal -force coefficient.
JL
qS
power coefficient,
Pn 3 !) 5
Cm thrust coefficient per propeller, —
Pn 2 D 4
X
longitudinal force coefficient, —
qS
c local wing chord parallel to the plane of symmetry
c* local wing chord normal to the reference sweep line
(See table I.)
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rb /2 2 ,
J c dy
wing mean aerodynamic chord, —
rb/2
I o c dy
wing-section design lift coefficient
center-of -gravity location
(See fig. 1(a).)
acceleration due to gravity
propeller diameter
maximum thickness of propeller blade section
horsepower per engine
incidence of the horizontal tail with respect to the wing-
root chord
propeller advance ratio, —
nD
tail length, distance between the quarter points of the mean
aerodynamic chords of the wing and of the horizontal tail
measured parallel to the plane of symmetry
free -stream Mach number
normal force per propeller
propeller rotational speed
a *
normal acceleration factor, -g
shaft power per motor
1 2
free -stream dynamic pressure, — PV
Reynolds number, based on the wing mean aerodynamic chord
propeller-tip radius
propeller-blade -section radius
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S
St
T
area of semi span wing
area of semispan tail
thrust per propeller parallel to the stream
T c
t
V
W
X
y
a
“t
3
3’
e
n
p
<p
thrust coefficient per propeller.
PV 2 D 2
q _t
dC
wing section maximum thickness
free -stream velocity
weight of assumed full-scale airplane
longitudinal force, parallel to stream and positive in a
dragwise direction
lateral distance from the plane of symmetry
angle of attack of the wing chord at the plane of symmetry
referred to herein as the wing -root chord
angle of attack of the tail
propeller blade angle measured at 0.70 tip radius
propeller-blade -section angle
effective downwash angle
propeller or propulsive efficiency.
Crp J
m
mass density of air
angle of local wing chord relative to the wing -root chord,
positive for washin, measured in planes parallel to the
plane of symmetry
tail efficiency factor (ratio of the lift-curve slope of the
horizontal tail when mounted on the fuselage in the flow
field of the wing to the lift-curve slope of the isolated
horizontal tail)
tail effectiveness parameter, measured for a given angle of
attack
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Subscripts
av
average
w
■wing
t
tail
MODEL AND APPARATUS
The semispan model represented the right-hand side of a hypotheti-
cal four-engine airplane. Figures 1(a) through 1(d) and table I present
dimensions and details of the model. Figure 2 shows the model mounted
in the wind tunnel. The selection of the geometric properties and the
details of the construction of the wing, nacelles, fences, tail, and
fuselage have been discussed in references 1, 2, and 3» The three-
bladed supersonic propeller, designated NACA l.l67~(0) (03) -058 and
having right-hand rotation, was specifically designed for the subject
investigation and is described in detail in reference 5« Figure 3
presents the propeller plan -form and blade -form curves.
The power to drive the propellers was supplied by a variable -speed
induction motor in each nacelle. Each motor had a normal rating of
75 horsepower at 18,000 revolutions per minute. The propellers were
driven through gears at a rotational speed 1.5 times that of the motors.
The shaft power delivered to the propellers was determined by measuring
the input power to the motors and applying corrections for the motor
and gearbox losses. Motor rotational speed was measured by means of an
electronic tachometer on each motor.
TESTS
Test Conditions
The longitudinal characteristics of the model were investigated
over a Mach number range of 0.60 to 0.90 at Reynolds numbers of 1,000,000
and 2,000,000. At each Mach number, tests were made with propeller blade
angles of tl° and 51° through an angle -of -attack range of 2° to 10°. At
each angle of attack, the propeller rotational speed was varied from
windmilling to the maximum obtainable, being limited by either maximum
motor speed or maximum motor power. Measurements of the static pressures
on the wind-tunnel walls during the tests at a Mach number of 0.90
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indicated the possibility of partial choking of the wind tunnel. It is
believed that the force and moment data shown at this Mach number are
partially affected by this phenomenon.
Tests were made at tail heights of 0 b/2 and 0.10 b/2 above the
fuselage center line. Tail incidences of -2°, -4°, and -6° were inves-
tigated at the Ob/2 tail position.
Propeller Calibration
The propeller was calibrated on a specially constructed calibration
nacelle which allowed the characteristics of the propeller, in the pres-
ence of the spinner and the nacelle forebody to be ascertained. Refer-
ence 5 presents the details of the calibration procedure and the results
of the calibration. Propeller normal -force characteristics were deter-
mined as part of the propeller calibration and are presented herein.
REDUCTION OF DATA
Thrust Coefficient
The model thrust coefficient, T c , used herein is the average for
the two propellers, and is obtained from the results of the propeller
calibration (ref. 5)* Advance ratios were computed for each of the
propellers, and the corresponding thrust coefficients were obtained
from the calibration results at a comparable Mach number, Reynolds
number, average propeller upflow angle (ref. 7), and propeller blade
angle. Typical variations of thrust coefficient with advance ratio for
one propeller (ref. 5) are shown in figure 4.
Adjustment to the advance ratios of the propellers operating on
the model was necessary since propeller blade angles could be duplicated
only to within ±0.15° between the propeller calibration and the present
test. In addition, it is probable that differences in the effective
propeller blade angles between the model and the calibration nacelle
existed because of slightly dissimilar radial distribution of upflow in
the plane of the propeller (ref. 7). The adjustment used was based on
the observed differences in windmilling advance ratios between propeller
operation on the model and on the calibration nacelle at comparable
geometric propeller blade angles and test conditions. It was assumed
that thrust as well as power was approximately equal at the windmilling
advance ratios for the two operations and that the small blade -angle
difference did not affect the rate of change of thrust coefficient with
advance ratio. Advance ratios measured for the propellers operating on
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the model were adjusted "by the difference between the windmilling
advance ratios measured for the propeller operating on the model and
on the calibration nacelle. Thrust coefficients for the powered model
were then obtained from the calibration results at these adjusted
advance ratios* These effects were generally small and changed the
propeller thrust coefficient by only 0.002 at the higher Mach numbers
and the larger thrust coefficients.
Force and Moment Data
The basic data obtained at various thrust coefficients at constant
angle of attack were reduced to conventional form and are presented as
lift coefficient as a function of angle of attack, and longitudinal
force coefficient and pitching -moment coefficient as functions of lift
coefficient. These variations with angle of attack and lift coefficient
were obtained by cross plotting the basic data for a lift-coefficient
and thrust-coefficient relationship corresponding to an assumed full-
scale power condition (fig. 5) &nd for constant thrust coefficient*
Corrections
The data have been corrected for constriction effects due to the
presence of the tunnel walls, for tunnel-wall interference originating
from lift on the wing, and for longitudinal force tares caused by aero-
dynamic forces on the exposed portion of the turntable upon which the
model was mounted.
The effects of wind-tunnel -wall constraint on the propeller slip-
streams were evaluated by the method of references 8 and 9 an( l were
found to be negligible. The dynamic pressure was corrected for con-
striction effects due to the presence of the tunnel walls by the method
of reference 10. These corrections and the corresponding corrections
to the Mach number are listed in the following table:
Corrected
Uncorrected
Corrected
Mach number
Mach number
^Uncorrected
0.60
0.598
1.006
.70
.695
1.009
.80
.793
1.011
.83
.821
1.013
.86
.848
i.oi4
• 90
.883
1.022
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Corrections for the effects of tunnel-wall interference originating
from the lift on the wing were calculated by the method of reference 11.
The corrections to the angle of attack and to the longitudinal force
coefficient showed insignificant variations with Mach number. The cor-
rections added to the data were as follows:
Aa = 0.38 C L
AC X = 0.0059 C L 2
The correction to the pitching -moment coefficient had significant varia-
tions with Mach number* The following corrections were added to the
pitching -moment coefficients:
AC m — Ki ^L-tail off (Tail off)
AC m - K x C Ltail Qff
C ^tail
8Cm
dit-
(Tail on)
The values of Kx and K 2 for each Mach number were calculated by the
method of reference 11 and are given in the following table:
M
Ki
k 2
0.60
0.0048
0.77
.70
.0057
.79
.80
.0069
.81
.83
.0073
.82
.86
.0078
.83
.90
.0087
.85
The correction constants for the tunnel -wall interference effects were
computed for propeller-off conditions since the effects of propeller
slipstream on wing lift and tail effectiveness were small over the Mach
number range of the investigation. However, the lift coefficients used
to determine the actual corrections were total values reflecting all
the propeller effects. Results of the propeller calibration indicated
the effects of propeller direct forces to be negligible.
Since the turntable upon which the model was mounted was directly
connected to the balance system, a tare correction to longitudinal
force was necessary. This correction was determined by multiplying the
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longitudinal force on the turntable, as determined from tests with the
model removed from the wind tunnel, by the fraction of the turntable
area not covered by the model fuselage. The following corrections
were subtracted from the measured longitudinal force coefficients:
M
^tare
0.60
•TO
.8o
.86
• 90
0.0025
.0026
.0028
.0030
.0032
No attempt has been made to evaluate tares due to interference between
the model and the turntable or to compensate for the tunnel -floor bound-
ary layer which, at the turntable, had a displacement thickness of one-
half inch.
RESULTS AND DISCUSSION
An index to the basic data is presented in table II. The basic
data are tabulated in tables III through XI, and the coefficients of
lift, longitudinal force, and pitching moment are plotted in conven-
tional form for constant values of thrust coefficient in figures 6 to 14
Figures 15 through 31 present, for selected conditions, the effects of
propeller operation, Mach number, tail height, Reynolds number, and
propeller blade angle on the longitudinal characteristics of the model.
Effects of Operating Propellers on the
Longitudinal Characteristics
The longitudinal characteristics of the model, with and without
operating propellers, are presented in figures 6 through lh. In general
the effects of the operating propellers were not large compared to the
propeller effects at low speed shown in reference 6. Compared to the
model without propellers, operation of the propellers at constant thrust
coefficients generally increased the lift-curve slopes and decreased the
static longitudinal stability. The term "static longitudinal stability,
as used herein, refers to the slopes of the curves of pitching-moment
coefficient as a function of lift coefficient. Decreases in stability
are indicated by reductions in the negative slopes of the curves . Gen-
erally, the trim lift coefficients increased with increasing thrust
coefficient but at any constant thrust coefficient they decreased with
increasing Mach number. There was no large effect of operating propel-
lers on the variation of longitudinal force coefficient with lift
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coefficient at lift coefficients less than about 0.1+0 or 0.50. It is
believed that the erratic variations shown in some of the longitudinal
force data at a Mach number of 0.90 are due, at least in part, to the
choking phenomenon previously mentioned.
The variations of the longitudinal characteristics with Mach number
are presented in figures 15, 16, and 17. These variations are shown at
lift coefficients of 0.20 and 0.1+0 for the model with the propellers off
and with the propellers operating at several constant values of thrust
coefficient.
Operation of the propellers increased the lift-curve slopes (fig. 15)
but, in general, had only small effects on the variation of lift-curve
slope with Mach number. At a lift coefficient of 0.1+0, operating the
propellers at a thrust coefficient of 0.03 increased the Mach number for
lift divergence from approximately O .83 to approximately 0.86.
Figure l6 shows the variation with Mach number of the increment of
longitudinal force coefficient above its value at a Mach number of 0.70
for several different values of propeller thrust coefficient and with
propellers removed. It was anticipated that the Mach number of longitu-
dinal force divergence would be decreased as a result of the increased
velocity behind the operating propellers. However, this effect did not
occur, and the Mach number for drag divergence was little affected by
operation of the propellers. At supercritical speeds, the drag rise
with increasing Mach number was reduced considerably with increase in
propeller thrust coefficient. This reduction was due, in part, to
increases in the wing lift-curve slope with the propellers operating.
Thus, the same lift coefficient can be obtained at a lower angle of
attack and this fact tended to reduce the shock-induced losses over the
outer portion of the wing span. It is also thought that some of the
effect stemmed from increases in the effective Reynolds numbers of the
wing sections immersed in the propeller slipstreams. It is doubtful
that a favorable Reynolds number phenomenon would prevail at full-scale
Reynolds numbers.
The effects of Mach number on the slopes of the pitching -moment
curves are presented in figure 17 at lift coefficients of 0.20 and 0.1+0
for the model with the propellers off and with the propellers operating
at several constant values of thrust coefficient. The effects of Mach
number were generally greater with the propellers operating than with
the propellers off. In general, the static longitudinal stability
decreased slightly with Mach number when the tail was on and increased
slightly when the tail was off up to a Mach number of approximately 0.82.
At higher speeds, changes in stability due to Mach number were inconsist-
ent and more pronounced.
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Effects of the Operating Propellers on the
Longitudinal. Stability
The factors which determine the static longitudinal stability of a
propeller -driven airplane are the stability with the propellers removed,
the direct propeller forces normal to and along the thrust axis, and the
effects of the propeller slipstream on the flow on the wing and at the
horizontal tail. Figures l8 and 19 show for several Mach numbers these
various effects of the operating propellers on tail-on and tail-off
static longitudinal stability at zero thrust, at a comparatively high
constant thrust coefficient, and at the conditions of constant horse-
power shown in figure 5* The data presented were obtained by adding
pitching -moment increments, referred to the center of gravity, due to
propeller thrust and normal force (from the propeller calibration data)
to the propellers -off pitching -moment data. This total was then sub-
tracted from the power-on pitching moments to ascertain approximately
the slipstream effects. For both constant thrust and constant power,
the various effects of the operating propellers on the pitching -moment
characteristics of the model were small. For the center -of -gravity
position shown on figure 1(a), normal force and thrust of the propellers
were generally destabilizing. The effects of the propeller slipstream
on the wing were generally destabilizing while their effects on the tail
were generally stabilizing.
Figure 20 presents, for a Mach number of 0.80 and a constant thrust
coefficient of 0.04, a comparison of the predicted and measured varia-
tions with angle of attack of the incremental pitching -moment coefficient
due to propeller normal force. The measured variations of increments of
pitching -moment coefficient with angle of attack due to propeller thrust
and propeller slipstream on the wing and tail are also shown. The effect
of propeller normal force on the pitching moment was calculated by the
method presented in the Appendix. The predicted pitching -moment incre-
ments due to the propeller normal force are in good agreement with the
measured effects. The small discrepancy at the lower angles of attack
is believed due to lift stemming from the asymmetry of the nacelle fore-
body. The theoretical computations did not account for any lift contri-
bution due to the nacelle forebody.
The effects of propeller slipstream on the pitching -moment charac-
teristics of the wing and tail could not be predicted to any acceptable
degree of accuracy with existing methods. It is believed that the com-
bination of the effects of wing sweepback, of viscous separation, of
propeller slipstream rotation, and of wing-nacelle interference makes
the estimation of slipstream effects on the pitching-moment character-
istics of the wing and tail virtually impossible for the present model.
Figure 21 shows the variation with Mach number of the various
effects of the operating propellers on the pitching -moment -curve
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slopes A(dC m /dCL). The data are presented for a representative lift
coefficient for level flight (C^ = 0 . 4o) and for constant thrust coef-
ficient and constant simulated horsepower. The effects of slipstream
on the horizontal tail were assumed to he the differences between tail-
on and tail -off slipstream effects. The effect of propeller normal
force varied with Mach number at constant horsepower because of the
relationship of thrust coefficient and lift coefficient used in calcu-
lating the conditions (fig. 5). The variations of the effects of the
propeller slipstream with Mach number were small, generally amounting
to a change in pitching -moment-curve slope of less than ±0.05.
Effects of the Operating Propellers on the Stability Contribution
of the Horizontal Tail
The horizontal -tail contribution to stability is a function of the
downwash factor 1 - (de/cia), the tail -efficiency factor ^(q.j./q) ,
( dC L+/ da t)
and the ratio is _ olated tail * Calculations were made using
(dC L /da) tail
off
the method of reference 12 to evaluate the effective downwash character-
istics and the tail efficiency factor with and without operating propel-
lers. The force data presented in figures 6 through 9 and the isolated
tail -force data presented in reference 3 were used for the computations
of effective downwash angle e, T]^(q^/q) , and the ratio
( dC Lt / da t \ sol a ted tail
and the results are shown for several Mach num-
(dCL/da) tail Qff
bers in figures 22, 23, and 2k as functions of angle of attack. It was
assumed for the computation of downwash angle € and tail-efficiency
factor ii^Cq^/q) that the Mach number at the tail was the same as the
free -stream Mach number . The effect of the propellers on downwash
amounted to a change in downwash angle of 0.5° or less. At high angles
of attack the effect of the operating propellers on the factors ^(q^/q)
(dC L /do,.).
and isolated ^ tail v&s however, these effects are
(d.e L / d a)t ai i off
compensating and their over-all effect on tail effectiveness was small
The variations with Mach number of the tail-effectiveness parameter,
dc m /dii, the isolated tail lift.-curve slope, and the various factors
affecting the stability contribution of the tail are shown in figures 25>
26, and 27 for a representative level flight, high-speed altitude (ct=4°) .
The effects of Mach number on 6c m /Si^ were small with and without the
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Ik
operatixig propellers. For the selected condition, operation of the pro-
pellers had little effect on the variations of the factors 1 - (de/d a),
r) t (q^/q) , and - — iso - Lat,ed vith Mach number.
(dC L /da) tail Qff
The effects of horizontal-tail height on the pitching -moment-curve
slopes of the model with and without operating propellers are shown in
figure 28 for several Mach numbers. Raising the horizontal tail
increased the static longitudinal stability slightly with the propellers
off at Mach numbers less than 0.90, but was destabilizing over the Mach
number range of the investigation with the propellers operating.
Propulsive Characteristics
Figure 29 presents for an upflow angle of approximately 0° and a
Mach number of 0.80, a comparison of the characteristics of the isolated
propeller (ref. 5) with the propulsive characteristics of the model.
Also shown is a comparison of the variations with Mach number of the
efficiency of the isolated propeller and the propulsive efficiency of
the model at a constant thrust coefficient of 0.04.
The propulsive characteristics include the lift due to the propel-
ler slipstream (ref. 13 ) and the effects of the operating propellers on
longitudinal force characteristics previously discussed. The propeller
is credited with these effects by calculating the effective thrust coef-
ficients and propulsive efficiencies of the model as follows:
CT effective ~ “ ( S A D ) J Cx props on Cx props off)
kprops on
and propulsive efficiency
C T e ffective ^
Figure 29 indicates that the effective thrust coefficients for
the conditions selected for the comparison were greater than the
thrust coefficients measured for the isolated propeller, and that the
corresponding propulsive efficiencies, consequently, exceeded the effi-
ciencies indicated for the isolated propeller. Generally, the propul-
sive efficiency increased with increasing Mach number while the effi-
ciency of the isolated propellers decreased slightly. This effect is
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believed to be associated with the decrease in the rate of change of
longitudinal force coefficient with Mach number indicated in figure 16.
In computing propulsive efficiencies, no distinction was made
between the effects of propeller slipstream and the effects of propeller
direct forces. However, for the range of Mach numbers and propeller
thrust coefficients of the subject investigation, the effects of propel-
ler direct forces on lift were negligible.
Longitudinal Characteristics of an Assumed Airplane
Figure 30 presents a summation of the longitudinal characteristics,
as calculated from the results of the subject investigation, of an
assumed airplane operating with the power required for level flight at
an altitude of 40,000 feet. These characteristics are presented as
functions of Mach number or normal -acceleration factor. The lift coef-
ficients shown are computed values based on a wing loading of 65 pounds
per square foot and the assumed airplane altitude.
The effects of propeller operation at the power for level flight on
the static longitudinal stability of the airplane were small (fig. 28).
Compared to propellers -off stability a maximum decrease in pitching-
moment -curve slope of 0.04 was indicated at a Mach number of 0.70. Only
a small change was indicated in the stable variation of tail incidence
for trim with Mach number between the conditions of propellers off and
propellers operating at the power required for level flight. At constant
Mach number, the variation of tail incidence for trim with normal accel-
eration was not greatly affected by the operation of the propellers at
the power required for level flight.
Effects of Reynolds Number and Propeller Blade Angle
Lift-curve slopes, pitching-moment-curve slopes, and longitudinal
force coefficients for the model at a lift coefficient of 0.40, with
and without operating propellers, are presented in figure 31 for
Reynolds numbers of 1,000,000 and 2,000,000 at Mach numbers of 0.70, 0.80,
and 0.90. These slopes and coefficients are also presented for propeller
blade angles of 4l° and 51° at Mach numbers of 0.70 and 0.80. The
effects of varying Reynolds number and propeller blade- angle on the lift-
curve slopes and pitching-moment-curve slopes were negligible at Mach
numbers of 0.70 and 0.80. Appreciable Reynolds number effects were evi-
dent on these slopes at a Mach number of 0.90« However, it is believed
that the data for this Mach number were affected by the partial choking
previously mentioned.
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Longitudinal force coefficients were only slightly affected by
changes of Reynolds number and of propeller blade angle at a Mach num-
ber of 0.70 and 0.80. At a Mach number of 0.90, increasing the Reynolds
number from 1 , 000,000 to 2 , 000,000 resulted in sizable decreases in
longitudinal force coefficient.
CONCLUSIONS
An investigation has been made of the effects of operating propel-
lers upon the longitudinal characteristics of a four-engine tractor
airplane configuration employing a wing with 4o° of sweepback and an
aspect ratio of 10. The Mach number range of the investigation was 0.60
to 0.90. The following conclusions were indicated:
1. The over-all effects of operating propellers on the longitu-
dinal characteristics at high subsonic speeds were not large when com-
pared to the effects of operating propellers at low speeds. The pro-
pellers operating at constant thrust coefficients generally resulted in
a reduction in the longitudinal stability. Increasing the propeller
thrust coefficient while maintaining a constant Mach number increased
both the longitudinal stability and the trimmed lift coefficient.
2. Operation of the propellers at constant thrust coefficient
increased the wing lift-curve slope but had little effect on the varia-
tion of lift-curve slope with Mach number.
3 . Operation of the propellers had little effect on the Mach num-
ber for longitudinal force divergence at a constant lift coefficient
but resulted in a decrease in the rate of change of longitudinal force
coefficient with Mach number at supercritical speeds. This effect
increased with increasing propeller thrust coefficient and with increas-
ing lift coefficient.
4 . It was possible to predict the effects of propeller normal
force on the longitudinal stability of the model with good accuracy.
However, the propeller slipstream effects on the wing and horizontal
tail could not be predicted with existing methods to any acceptable
degree of accuracy.
5. Raising the horizontal tail had little effect on the longitu-
dinal stability with the propellers removed but was destabilizing with
the propellers operating.
6 . For an assumed airplane, operating at the power required for
level flight at an altitude of 40,000 feet, calculations indicate only
CONFIDENTIAL
NACA KM A53J23
CONFIDENTIAL
17
a small change in the stable variation of tail incidence for trim with
either Mach number or normal acceleration compared to the propellers-
off condition.
Ames Aeronautical Laboratory
National Advisory Committee
Moffett Field, Calif.,
for Aeronautics
Oct. 23, 1953
CONFIDENTIAL
18
CONFIDENTIAL
NACA RM A53J23
APPENDIX
CALCULATION OF PROPELLER NORMAL FORCE
Isolation of propeller effects on the longitudinal stability of an
airplane requires either a knowledge of the normal-force characteristics
of the propeller or a suitable method of calculating those characteris-
tics. The method used herein for predicting propeller normal force is
presented in this Appendix in addition to experimental normal-force data
obtained with the calibration nacelle reported in reference 5.
Presented in figure 32 is propeller normal-force coefficient as
a function of upflow angle at 0.7 propeller radius for the
NACA 1. l67- ( 0 ) ( 03 ) -058 three-blade propeller used in this investigation.
Shown in figure 33 for a representative blade angle and Mach number at
an upflow angle of 5° is a comparison of the experimental and theoretical
variation of normal -force -curve slope with thrust coefficient. It may
be noted that the agreement between the theoretical and experimental
slopes is good, the theoretical values being approximately 95 percent
of the experimental normal -force -curve slopes.
The method used in calculating propeller normal force, which was
proposed by Messrs. Vernon L. Rogallo and John L. McCloud III of the
Ames Aeronautical Laboratory, is based on the relationship of the pro-
peller normal force to the oscillating torque -producing components of
force on the blades as they operate in the nonuniform flow field. This
can be expressed as follows:
where
Cjj normal -force coefficient.
qjiD 2
D propeller diameter, ft
V
J advance ratio, —
Cf x amplitude of 1 X P variation of torque -force coefficient
N normal force, measured perpendicular to thrust axis, lb
X radial location of blade section, —
R'
CONFIDENTIAL
NACA RM A53J23
CONFIDENTIAL
19
X s spinner radius, fraction of tip radius
w fi phase angle of 1 x P variation of torque force
If it is assumed that there are no odd-order variations of torque force
ahove the fundamental, the product ( cp ^ cos can he found by the
following relationship:
(= fl cos a fl ) x . 1/2 (c W - c f(!=a7o o)
where
n angular position about the thrust axis, measured counterclockwise
from the upper vertical position as seen from the front, deg
The torque force coefficient can be calculated by its relationship to
the thrust coefficient, that is,
Cf = c-t tan (cp + 7)
The formula for computing the thrust coefficient is the same as given
in reference 1^, except that is replaced by ±A and is as follows:
V» sin A \ g
nnDX /
C tfl=90, 270°
= Krt 3 X 3 ^ cot cp - tan 7
57
•3 f a i \
( cot cp + )
^ 57.3/
where
A upflow angle, angle of local flow at 0.7 propeller radius and at
the horizontal center line of the propeller, measured with
respect to the thrust axis in a plane parallel to the plane of
symmetry, deg
c+ section thrust coefficient, - hr ^ L - 3 - i:
pn 2 D 4
K Goldstein correction factor for finite number of blades
r radius to blade section, ft
R* propeller radius, ft
CONFIDENTIAL
20
CONFIDENTIAL
NACA RM A53J23
ai propeller induced angle of inflow, deg
7 tan -1 / , ^ a< ^ e ~ sec ^ : ^ on ( ^ ra g
\ blade -section lift /
<P
cp Q + cti, deg
tan-< v ’ ;P 3 A ^
\ JtnDX ± V’ sin A/
V* local velocity, ft /sec
and where both + and - signs are indicated, the + is for ft =
the - is for Q = 270°.
90° i
and
CONFIDENTIAL
NACA RM A53J23
CONFIDENTIAL
21
REFERENCES
1. Tinling, Bruce E. , and Lopez, Armando E.: The Effects of Nacelles
and of Extended Split Flaps on the Longitudinal Characteristics
of a Wing -Fuselage -Tail Combination Having a Wing With 40° of
Sveepback and an Aspect Ratio of 10. NACA RM A53D06, 1953*
2. Edwards, George G., Tinling, Bruce E., and Ackerman, Arthur C.: The
Longitudinal Characteristics at Mach Numbers up to 0.92 of a Cam-
bered and Twisted Wing Having 40° of Sweepback and an Aspect Ratio
of 10. NACA RM A52F18, 1952.
3* Tinling, Bruce E.: The Longitudinal Characteristics at Mach Numbers
up to 0.9 of a Wing -Fuselage -Tail Combination Having a Wing With 40°
of Sweepback and an Aspect Ratio of 10. NACA RM A52I19, 1952.
4. Boltz, Frederick W., and Shibata, Harry H.: Pressure Distribution
at Mach Numbers up to 0.90 on a Cambered and Twisted Wing Having 40°
of Sweepback and an Aspect Ratio of 10, Including the Effects of
Fences. NACA RM A52K20, 1953-
5. Demele, Fred A., and Otey, William R. : Investigation of the
NACA l.l67-(0)(03)-058 and the NACA l.l67-(0) (05)-058 Three-Blade
Propellers at Forward Mach Numbers to 0.92 Including Effects of
Thrust-Axis Inclination. NACA RM A53F16, 1953.
6 . Edwards, George G., Buell, Donald A., and Dickson, Jerald K.: The
Results of Wind-Tunnel Tests at Low Speeds of a Four-Engine
Propeller-Driven Airplane Configuration Having a Wing With 40° of
Sweepback and an Aspect Ratio of 10. NACA RM A53I28 , 1953*
7* Lopez, Armando E., and Dickson, Jerald K.: The Effects of Compres-
sibility on the Upwash at the Propeller Planes of a Four-Engine
Tractor Airplane Configuration Having a Wing With 40° of Sweepback
and an Aspect Ratio of 10. NACA RM A53A30a, 1953*
8 . Glauert, H.: The Elements of Aerofoil and Airscrew Theory.
MacMillan Company, 1943, PP- 222-226.
9 . Young, A. D.: Note on the Application of the Linear Perturbation
Theory to Determine the Effect of Compressibility on the Wind
Tunnel Constraint on a Propeller. R.A.E. TN No. Aero. 1539
(British), Nov. 1944.
10. Herriot, John G.: Blockage Corrections for Three-Dimensional -Flow
Closed-Throat Wind Tunnels, With Consideration of the Effect of
Compressibility. NACA Rep. 995, 1950 . (Formerly NACA RM A7B28)
CONFIDENTIAL
CONFIDENTIAL
NACA RM A53J23
11. Sivells, James C., and Salmi, Rachel M.: Jet-Boundary Corrections
for Complete and Semispan Svept Wings in Closed Circular Wind
Tunnels. NACA TN 2k^>k, 1951.
12. Johnson, Ben H., Jr., and Rollins, Francis W. : Investigation of a
Thin Wing of Aspect Ratio 4 in the Ames 12-Foot Pressure Wind
Tunnel. V - Static Longitudinal Stability and Control Throughout
the Subsonic Speed Range of a Semispan Model of a Supersonic
Airplane. NACA RM A9I01, I 9 L 9 .
13. Betz, A.: Considerations on Propeller Efficiency. NACA IM 48l,
1928.
1^. Roberts, John C., and Yaggy, Paul F.: A Survey of the Flow at the
Plane of the Propeller of a Twin-Engine Airplane. NACA TN 2192,
1950.
CONFIDENTIAL
NACA RM A53J23
CONFIDENTIAL
23
TABLE I.- GEOMETRIC PROPERTIES OF THE MODEL
Wing
Reference sweep line: Locus of the quarter-chord, points of
sections inclined 40° to the plane of symmetry
Aspect ratio (full-span wing) 10.0
Taper ratio 0.4
Sweepback 40°
Twist -5°
Reference sections (normal to reference sweep line)
Root NACA 0014, a=0.8 (modified) ^=0.4
Tip NACA 0011, a=0.8 (modified) Cj^O.4
Area (semispan model) 6.944 ft 2
Mean aerodynamic chord 1.251 ft
Incidence (measured in the plane of symmetry) 3°
Fences at y/b/2 = 0.33# 0.50, 0.70, and 0.85
(See fig. 1(d) for fence details.)
Nacelles
Frontal area (each) 0.208 ft 2
Inclination (measured with respect to wing root chord)
Inboard -6. 5°
Outboard . .......... -7»0°
Propellers
Diameter 1.167 ft
Number of blades ..... 3
Propeller-activity factor (per blade). 188.4
Propeller-blade thickness -chord ratio (0.70 radius) 0.03
Solidity (per blade) 0.058
Blade sections Symmetrical NACA l6 series
Horizontal Tail
Reference sweep line: Locus of quarter-chord points of sections
inclined 40° to the plane of symmetry
Aspect ratio (full -span tail)
Taper ratio
Sweepback
Reference section (normal to reference sweep line)
Tail length, Z-fc . •
. . 4.5
. . 0.4
. . 40°
NACA 0010
. 3.25c
CONFIDENTIAL
24
CONFIDENTIAL
KACA RM A53J23
TABLE I.- GEOMETRIC PROPERTIES OF THE MODEL - Concluded
Horizontal Tail (Continued)
Area (semi span model)
Mean aerodynamic chord ....
Tail volume, Z-^/c (St/Sy) . . .
Tail heights (measured vertically from the fuselage
center line to the hinge axis
of the horizontal tail
(see fig. 1(a))
0, 0.10 h/2
Fuselage
Fineness ratio
Frontal area (semispan model) .
Fuselage coordinates:
Distance from
nose, in.
Radius, in.
0
0
1.27
1.04
2.54
1.57
5.08
2.35
10.16
3.36
20.31
4.44
30.47
4.90
39.44
5.00
50.00
5.00
60.00
5.00
70.00
5.00
76.00
4.96
82.00
4.83
88.00
4.6l
94.00
4.27
100.00
3-77
106.00
3.03
126.00
0
CONFIDENTIAL
4C
MCA RM A53J23
CONFIDENTIAL
25
TABLE II,- INDEX OF TABLES AND FIGURES REPRESENTING
THE BASIC LONGITUDINAL DATA
Table
Figure
Tail
height
it,
leg
P,
deg
R,
million
M,
range
III
6
-2
51
1
0.70 to 0.90
IV
7
-k
51
1
0.70 to 0.90
V
8
°l
-6
51
1
0.70 to 0.90
VT
9
tail off
—
51
1
0.70 to 0.90
VII
10
°* 10 |
-k
51
1
0.70 to 0.90
VIII
11
°I
-k
51
2
0.70 to 0.90
IX
12
tail off
—
51
2
0.70 to 0.90
X
13
0 —
2
-k
kl
2
0.60 to 0.80
XI
Ik
tail off
—
kl
2
0.60 to 0.80
CONFIDENTIAL
CONFIDENTIAL
TABLE III.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 1+0° OF SWEEFBACK AND AN ASPECT RATIO OF 10} TAIL HEIGHT * 0 u/2, it = -2°,
p = 51°, R = 1,000,000
(a) M = 0.70, 0.80, 0.83
M, 0.70
M, 0.80
M, 0.83
a
cl
Cx
Cm
*C«T
Jar
°Pay
a
cl
Cx
c*
T ‘ay
Jav
<*ay
a
c L
Cx
Cm
T c a y
Jay
^ay
•2.04
0.159
0.0216
-0.0218
■2.04
0.170
0.0250
-0.0220
- - *
. _ _
*2.04
0.173
0.0261
-0.0199
—
2.04
.148
.0242
-.0343
-0.003
2.772
...
2.04
• 157
.0275
-.0387
-o.oo4
2.751
- - -
2.04
.165
.0295
-.0394
-0.004
2.745
- - -
2.04
.147
.0139
-.0279
.009
2.535
0.231
2.04
.157
.0185
-.0297
.007
2.538
0.199
2.04
.162
.0193
-.0308
.010
2.510
0.207
2.03
.143
.0024
-.0176
.024
2.323
.413
2.04
.155
.0091
-.0207
.019
2.350
.357
2.04
.160
.0091
-.0196
.021
2.3U
.376
2.03
.142
-.0103
-.0068
.o4i
2.121
.564
2.04
.154
-.0029
-.0108
.034
2.139
.499
2.04
.159
-.0016
-.0085
.036
2.112
.495
2.03
.141
-.0236
-.0013
.058
1.944
.655
2.04
.153
-.0148
-.0045
.049
1.964
.594
2.04
.159
-.0138
-.0025
.049
1.917
.584
a 3.07
.259
.0222
-.0405
„
_ _ _
*3.08
.279
.0253
-.0417
*3.08
.287
.0269
-.0412
—
—
—
3-07
.254
.0249
-.0479
-.002
2.771
_ _ •
3.07
.271
.0263
-.0527
-.004
2.749
- - -
3.08
.282
.0305
-.0532
-.003
2.726
- - -
3.06
.251
.0144
-.0399
.010
2.529
.234
3-07
.271
.0196
-.0456
.007
2.549
.191
3.08
.282
.0206
-.0438
.007
2.520
.208
3.06
.251
.0031
-.0341
.024
2.329
.415
3-07
.272
.0098
-.0367
.019
2.354
.354
3.08
.283
.0112
-.0368
.018
2.328
.361
3.06
.252
-.0101
-.0288
.041
2.123
.568
3.07
.275
-.0015
-.0314
.034
2.153
.498
3.08
.284
-.0006
-.0305
.033
2.125
.502
3.07
.253
-.0228
-.0257
.057
1.945
.659
3.07
.276
-.0129
-.0275
.048
1.974
.592
3.08
.286
-.0124
-.0275
.046
1.925
.588
*4.lo
.358
.0242
-.0577
*4.11
.390
.0277
-.0582
^ - -
*4.11
.402
.0306
-.0599
—
—
—
4.09
• 352
.0266
-.0622
-.002
2.774
-.- -
4.10
.365
.0310
-.0777
-.004
2.743
- - -
4.11
.399
.0343
-.0651
-.003
2.742
- - -
4.09
.354
.0160
-.0558
.011
2.519
.241
4.10
.383
.0224
-.0569
.007
2.550
.187
4.11
.402
.0242
-.0607
.008
2.524
.209
4.10
• 358
.0049
-.0516
.025
2.328
.423
4.11
.388
.0136
-.0531
.018
2.362
.349
4.11-
.405
.0145
-.0548
.020
2.329
.373
4.10
.361
-.0085
-.04l8
.042
2.128
•571
4.11
.390
.0012
-.0493
.034
2.153
.500
4.11
.4n
.0042
-.0498
.034
2.135
.493
4.10
.365
-.0209
-.0432
-.057
1.950
.663
4.11
• 395
-.0097
-.0464
.047
1.985
• 595
4.12
.416
-.0084
-.0470
.049
1.930
.587
•5.12
.456
.0271
-.0767
_ _ _
*5.14
.497
•0334
-.0772
—
*5.14
.508
.0399
-.0781
—
—
—
5.12
.452
.0298
-.0763
-.002
2.774
_ _ _
5.14
.496
.0362
-.0787
-.004
2.748
5.14
.511
.0421
-.0818
-.003
2.742
- - -
5.12
• 453
.0192
-.0722
.010
2.531
.227
5.14
.497
.0279
-.0751
.007
2.560
.183
5.14
.514
.0324
-.0783
.008
2.525
.210
5.12
.460
.0084
-.0676
.025
2.332
.418
5.14
.501
.0180
-.0721
.019
2.366
.358
5-15
.520
.0229
-.0749
.020
2.331
.372
5.13
.466
-.0056
-.0635
.043
2.117
•581
5.14
.507
.0064
-.0690
.034
2.154
.508
5-15
.526
.0133
-.0719
.034
2.140
.500
5-13
.471
-.0165
-.0599
.057
1-957
.662
5.14
.513
-.0048
-.0659
.049
1.980
.603
5.15
•533
.0008
-.0698
.048
1.941
• 597
*6.15
.556
.0315
-.0992
_ _ _
- - -
*6.16
.595
.0443
-.1002
*6.16
• 591
.0539
-.0928
—
—
—
6.15
• 551
.0340
-.0947
-.001
2.776
...
6.17
.600
.0460
-.0951
-.003
2.758
- —
6.17
.606
.0552
-.0929
-.003
2.753
6.15
.556
.0241
-.0890
.011
2.526
.238
6.17
.604
.0376
-.0930
.008
2.570
.162
6.17
.612
.0449
-.0920
.009
2.538
.185
6.15
•563
.0126
-.0846
.027
2.322
.433
6.17
.610
.0286
-.0902
.020
2.369
.360
6.17
.616
.0375
-.0889
.021
2.339
.371
6.16
•571
.0006
-.0797
.043
2.121
•579
6.17
.613
.0169
-.0871
.035
2.157
.506
6.17
.622
.0280
-.0857
.035
2.142
• 503
6.16
.578
-.0105
-.0758
.057
1.958
.665
6.17
.621
.0072
-.0856
.048
2.001
.602
6.18
.631
.0136
-.0842
.049
1.949
.599
*r.i8
.648
.0383
-.1240
_ _ _
. • -
_ - _
*7.18
.673
.0593
-.1155
*7.18
.660
.0692
-.0999
—
—
—
7.17
.648
-.1106
-.001
2.783
...
7.19
.690
.0606
-.1049
-.004
2.764
- - -
7.19
.682
.0724
-.0952
-.004
2.770
- - -
7.16
.653
!o310
-.1059
.012
2.536
.238
7.20
.698
.0525
-.1019
.007
2.574
.184
7.19
.689
.0629
-.0943
.009
2.536
.212
7.18
.662
.0207
-.1012
.026
2.335
.425
7.20
.702
.0429
-.1009
.020
2.374
.367
7.19
.691
.0541
-.0926
.021
2.336
.377
7.18
.672
.0088
-.0963
.044
2.126
.57 8
7 .20
.706
.0330
-.0995
.035
2.163
.510
7.20
.699
.0436
-.0907
.036
2.147
.512
7.19
.680
-.0013
-.0925
.058
1.963
.664
7.20
.713
.0244
-.0970
.048
2.004
.601
7.20
.709
.0344
-.0892
.048
1.963
.595
*8.20
•737
.0514
-.1452
*8.19
.728
.0785
-.1218
*8.19
.717
.0874
-.1133
—
—
—
8.20
.740
.0506
-.1275
-.002
2.793
8.20
.752
.0793
-.1050
-,oo4
2.778
- - -
8.20
.745
.0899
-.0975
-.004
2.767
8.20
.747
.0422
-.1180
.013
2.536
.241
8.21
.766
.0720
-.1041
.007
2.583
•193
8.21
.761
.0823
-.0995
.008
2.547
.213
8.20
.754
.0320
-.1119
.026
2.338
.425
8.21
.772
.0625
-.1007
.020
2.367
.368
8.21
.767
.0737
-.0979
.020
2.341
• 381
8.21
.764
.0203
-.1062
.044
2.127
.583
8.21
.778
.0528
-.0991
.035
2.163
• 517
8.21
.776
.0631
-.0971
.035
2.140
• 517
8.21
.77 2
.0113
-.1038
.059
1.963
.684
8.22
.786
.0433
-.0997
.047
2.009
.606
8.21
.786
.0540
-.0982
.047
1.970
.597
*9.21
.799
.0718
-.1632
_ _ _
*9.20
.778
.1000
-.1471
*9.20
.774
.1096
-.1384
—
—
—
9.22
.815
.0691
-.1382
-.001
2.793
9.21
.808
.1000
-.1134
-.00 4
2.782
- —
9.22
.805
.1127
-.1144
-.005
2.787
- —
9.22
.826
.0589
-.1271
.014
2.532
.261
9.22
.828
.0920
-.1113
.006
2.573
.208
9.22
.825
.1033
-.1092
.008
2.546
.225
9.22
.833-
.0492
-.1218
.027
2.332
.434
'9.23
.837
.0841
-.1094
.018
2.379
.371
9-23
.841
.0978
-.1068
.020
2.355
.381
9.23
.843
.0392
-.1149
.044
2.135
.582
9.23
•839
.0760
-.1111
•033
2.170
.518
9.23
.843
.0880
-.1044
.035
2.150
.518
9.23
.853
•0293
-.1100
.059
1.970
.669
9.23
.843
.0666
-.1134
.046
2.021
.601
9.23
.857
.0778-
-.1046
.047
1.982
.585
*10.22
.851
.0948
-.1679
*10.21
.826
.1266
-.1742
- _ .
*10.21
.809
.1341
-.1777
—
—
10.23
.881
.0928
-.1405
-.001
2.813
_ . .
10.22
.854
-.1250
-.1281
-.oo4
2.794
- - -
10.22
.851
.1359
-.1276
-.005
2.802
- - -
10.23
.866
.0827
-.1347
.013
2.543
.269
10.23
.865
.1176
-.1308
.006
2.580
.210
10.23
.868
.1281
-.1263
.003
2.556
.233
10.24
.896
.0724
-.1252
.027
2.325
.451
10.23
.884
.1092
-.1241
.018
2.382
•375
10.24
.885
.1188
-.1221
.019
2.358
.386
10.24
.908
.0628
-.1160
.044
2.133
.587
10.24
.896
.0991
-.1180
.035
2.163
•531
10.23
.883
.1101
-.1275
.035
2.154
.526
10.25
.919
•0538
-.1070
.058
1.978
.667
10.24
•903
.0934
-.1172
.045
2.030
.604
10.24
.892
.1036
-.1334
.046
1.997
.596
CONFIDENTIAL NACA RM A53J23
CONFIE
TABLE III.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 40° OF SWEEPBACK AND AN ASPECT RATIO OF 10 j TAIL HEIGHT = 0 t>/2, it = -2°,
p * 51°, R » 1,000,000 - Concluded
(L) M * 0.86, 0.90
M, 0.86
M, 0.90
a
Cl
c x
Cm
T ‘av
Jav.
CPav -
a
cl
Cx
Cb
T cav
Jav.
C Pav.
a 2.05
0.184
0.0286
-0.0186
*2.05
0.185
0.0388
-0.0138
2.05
.176
.0323
-.0414
-0.005
2.751
- - -
2.05
• 192
.0425
-.0554
-0.005
2.721
...
2.0*
.173
.0228
-.0300
.008
2.513
0.209
2.05
.189
.0282
-.0416
.009
2.42 6
0.238
2.04
.170
.0096
-.0164
.023
2.252
.402
2.05
.187
.0208
-.0319
.018
2.235
• 351
2.04
•171
-.0005
-.0063
• 035
2.061
.498
2.05
.186
.0106
-.0214
.027
2.037
• 433
2.04
.170
-.0100
-.0003
.047
1.897
•553
2.05
.186
.0020
-.0127
•037
1.868
.482
a 3.o8
• 303
.0312
-.0423
*3.08
•275
.0443
-.0347
...
3.08
.297
.0341
-.0554
-.005
2.756
- - -
3.08
.298
.0481
-0775
-.005
2.726
...
3.08
.298
.0247
-.0475
.008
2.516
.210
3-09
.305
.0350
-.0658
.008
2.457
•235
3.08
.301
.0045
-.0307
.031
2.133
.493
3-09
.307
.0257
-.0573
.017
2.253
•353
3.08
• 303
.0021
-.0296
.036
2.061
.508
3-09
.308
.0178
-.0526
.027
2.052
.437
3.08
.304
-.0080
-.0251
.046
1.910
•565
3-09
.313
.0097
-.0485
.03 6
1.889
.479
Vll
.410
.0379
-.0593
—
*4.10
.369
.0525
-.0546
...
_ _ ,
4.12
.415
.0396
-.0731
-.004
2.747
- - -
4.11
• 399
.0558
-.0914
-.005
2.736
_
4.12
.421
.0302
-.0663
.009
2.503
.228
4.11
• 396
.0462
-.0812
.009
2.452
• 235
4.12
.426
.0189
-.0606
.023
2.260
.405
4.11
.406
.0339
-.0760
.018
2.254
• 373
4.12
.431
.0096
-.0571
.036
2.064
.509
4.11
.412
.0243
-0735
.027
2.069
.455
4.12
.434
-.0008
-.0541
.046
1.923
.569
4.12
.417
.0184
-.0727
.036
1.893
.485
a 5.l4
.502
.0494'
-.0740
*5-12
•455
.0668
-.0666
_ _ .
- - -
_ _ _
5.15
• 516
.0526
-.0890
-.004
2.758
...
5-13
.476
.0677
-.0931
-.004
2.747
_ - _
5.15
.518
.0426
-.0819
.009
2.518
.223
5-13
.483
.0557
-.0866
.011
2.419
.261
5-15
•523
.0303
-.0775
.024
2.259
.416
5-14
.490
.0460
-.0848
.019
2.223
• 393
5.15
•529
.0200
-.0747
.037
2.059
.521
5-14
.500
.0386
-.0826
.029
2.022
.460
5.15
•533
• 0135
- .0742
.046
1.929
.563
5.14
• 505
.0316
-0833
.036
1.886
.493
a 6.l6
• 574
.0641
-.0825
*6.14
.532
.0798
-0792
_ _ _
- - -
_ _ _
6.17
• 596
.0667
-.0924
-.004
2.760
...
6.15
.547
.0829
-0932
-.004
2.750
- _ _
6.17
.601
.0566
-.0902
.009
2.518
.229
6.15
.561
.0702
-0931
.011
2.421
.273
6.17
.607
.0457
-.0877
.024
2.266
.417
6.16
• 568
.0635
-.0942
.020
2.232
.386
6.17
.614
.0365
-.0856
.03 6
2.076
.519
6.16
• 583
.0518
-.0949
.030
2.024
.471
6.17
.620
.0287
-.0847
.046
1-937
• 570
6.16
• 591
.0467
-0955
.036
1.891
.503
V .it
.642
.0817
-.0934
*7.16
.602
.0977
-0934
_ _ _
- - -
7.18
.670
.0943
-.0927
-.004
2-772
...
7.17
.630
.1011
-.1064
-.004
2.762
- - -
7.18
.669
.0744
-.0940
.010
2.519
.233
7.17
.636
.0883
-.1025
.011
2.439
.271
7.19
.682
.0628
-.0919
.024
2.268
.424
7.18
.647
.0796
-.1055
.021
2.229
.397
7.19
.689
•0537
-.0909
.037
2.072
.528
7.18
.656
.0731
-1075
.030
2.038
.468
7-19
.696
.0466
-.0910
.047
1.940
.576
7.18
.664
.0694
-.1082
•035
1.926
.496
a 8.l9
.705
.0997
-.1121
_ _ _
*8.18
.687
.1169
-.1248
- - -
_ _ _
8.20
• 731
.1030
-.1019
-.004
2.768
- - -
8.19
.696
.1204
-.1183
-.004
2.773
...
8.10
.746
.0947
-.1027
.009
2.526
.236
8.19
.716
.1064
-.1213
•Oil
2.440
.279
8.10
•756
.0829
-.1015
.023
2.274
.424
8.19
.724
.1002
-1195
.020
2.243
.401
8.11
.764
.0745
-.1021
•037
2.068
•531
8.20
• 732
.0952
-.1251
.029
2.055
.467
8.11
.772
.0688
-.1027
.048
1.957
•571
8.20
.741
.0882
-.1261
•035
1.939
.485
*9-20
.768
.1212
-.1421
*9.19
.746
.1413
-.1636
9.21
•793
• 1253
-.1218
-.005
2.791
...
9.20
• 765
.1403
-.1451
-.005
2.784
- - .
9-22
.814
.1172
-.1170
.009
2.530
.244
9-21
.787
.1360
-.1465
.010
2.469
.260
9.22
.827
.1044
-.1164
.024
2.270
.434
9.21
• 799
.1256
-.1420
.020
2.259
.406
9.23
• 835
.1008
-.1139
•037
2.082
• 530
9.22
.808
.1161
-1371
.029
2.065
.489
9.23
.842
.0927
-1135
.045
1.968
• 570
9.22
.811
.1140
-.1423
.035
1.960
.514
a 10.21
.805
.1476
-.1748
...
...
...
*10.21
.808
.1655
-1983
_ _ _
10.22
.851
.1495
-.1365
-.005
2.816
—
10.22
.837
.1688
-.1748
-.005
2.807
10.23
.880
.1403
-.1285
•Oil
2.526
.252
10.23
.869
.1604
-1707
.011
2.469
.278
10.24
.892
.1334
-.1250
.025
2.276
.437
10.23
.876
.1541
-.1669
.021
2.253
.415
10.24
.901
.1230
-.1233
.038
2.082
•537
10.23
.879
.1442
-.1658
.029
2.092
.475
10.24
• 903
.1189
-.1217
.046
1.972
.568
10.24
.885
.1398
-.1657
.036
1.960
.517
ro
-^1
NACA RM A53J23 CONFID!
confid:
TABLE IV.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING ro
A WING WITH to 0 OF SWEEPBACK AND AN ASPECT RATIO OF 10; TAIL HEIGHT = 0 L/2, it = -4°,
8 - 51°, R - 1,000,000
(a) M = 0.70, 0.80, 0.83
K, 0.70
M, 0.80
M, O.83
a
CL
Cx
c.
Tcav
Jav„
Cp av
a
c L
Cx
c»
T =av
J«y
C Pav
a
C L
cx
Cm
^av
Jav
C Pav
*2.03
0.140
0.0216
0.0446
*2.04
0.149
0.0246
0.0426
...
_ _ .
*2.04
0.154
0.0269
0.0470
2.03
2.03
.131
.127
.0248
.0137
.0233
.0321
-0.003
.009
2.770
2.530
0.243
2.03
2.03
.140
.138
.0282
.0188
.0190
.0286
-0.004
.007
2.755
2.542
0.203
2.04
2.04
.146
.142
.0297
.0212
-0.00k
.008
2.751
2.539
0.188
.124
.0007
.0455
.025
2.294
.438
2.03
.136
.0048
.0437
.024
2.278
.422
2.04
.141
.0117
.0391
.019
2.349
.346
.121
-.0133
.0597
.044.
2.086
• 588
2.03
.135
-.0064
.0534
.039
2.088
.541
2.04
.140
-.0006
.0525
.035
2.124
.496
2.03
.120
-.0251
.0676
.059
1.928
.664
2.03
.135
-.0124
.0573
.046
1.998
.584
2.04
.138
-.0117
.0610
.048
1.948
.575
*3.06
.243
.0220
.0195
_
*3.07
.261
.0249
.0170
*3.07
.268
.0272
.0230
—
—
.233
.0252
.0071
-.002
2.775
• « .
3.06
.251
.0287
.0031
-.004
2.755
- - -
3.07
.262
.0302
.0038
-.003
2.752
- - -
.235
.0162
.010
2.524
3.06
.251
.0183
.0132
.008
2.537
.211
3.07
.261
.0223
.0123
.006
2.566
.171
3.06
.235
' -.0001
.0296
.029
2.276
.459
3.06
.252
.0064
.0247
.024
2.291
.412
3-07
.262
.0126
.0215
.018
2.361
.345
3.06
.236
-.0129
.0363
.044
2.089
•595
3.06
.254
-.0057
.0314
.039
2.096
.539
3.07
.265
-.0004
.0329
.035
2.121
.505
3.06
.236
-.0247
.0402
.059
1.931
.669
3.07
.255
-.0111
.0349
.046
2.008
.587
3.07
.265
-.0095
.0386
.047
1.970
.574
“4.09
.341
.0237
.0009
*4.10
.370
.0270
-.0004
...
*4.10
.384
.0308
.0039
—
4.09
.335
.0270
-.0067
-.002
2.771
...
4.10
.362
.0307
-.0086
-.004
2.760
- - -
4.10
• 381
.0340
-.0095
-.003
2.745
- —
4.09
• 335
.0168
.0011
.009
2.540
.221
4.10
.365
.0211
-.0002
.008
2.538
.209
4.11
• 385
.0272
-.0041
.006
2.578
.149
4.09
.339
.0026
.0089
.027
2.295
.442
4.10
.370
.0091
.0078
.024
2.297
.409
4.10
.384
.0160
•0053
.018
2.361
.344
4.09
.3*2
-.0102
.0141
.044
2.049
•583
4.10
.375
-.0017
.0133
.038
2.109
.533
4.11
.388
.0020
.0132
.036
2.112
.512
4.09
• 3*5
-.0225
.0183
• 059
1.927
.666
4.10
.378
-.0079
.0159
.046
2.008
.584
4.11
• 392
-.0063
.0160
.046
1.971
.579
a 5 .12
.440
.0264
-.0169
- - -
*5.13
.478
.0324
-.0183
...
- - -
_ _ _
*5.14
.490
.0402
-.0141
—
—
- - -
5.12
.435
.0297
-.0189
-.002
2.767
_ _ .
5.13
.474
.0352
-.0243
-.003
2.763
_ . -
5.14
.494
.0416
-.0269
-.003
2.7*3
- - ■
5.12
.437
.0195
-.0151
.010
2.534
.218
5.13
.481
.0271
-.0419
.008
2.552
.201
5.14
.497
.0337
-.0195
.004
2.565
.177
5.12
.444
.0050
-.0079
.029
2.285
.458
5.14
.485
.0134
-.0102
.025
2.291
.419
5.14
.500
.0240
-.0151
.016
2.357
.351
5.12
.450
-.0069
-.0013
.045
2.091
• 582
5.14
.490
.0037
-.0060
.038
2.124
.530
5-14
.507
.0109
-0093
.032
2.119
.515
5.12
.*55
-.0187
.0014
.059
1.928
.665
5.14
.494
-.0027
-.0037
.046
2.020
• 587
5.14
• 513
.0032
-.0064
.043
1.977
• 579
*6.14
• 538
.0303
-.0383
_ _ _
...
*6.16
.577
.0433
-.0399
...
*6.16
• 570
.0531
-.0281
—
6.14
• 533
.0333
-.0360
-.001
2.773
- - -
6.16
.580
.0439
-.0372
-.003
2.771
- - -
6.16
.588
.0531
-.0368
-.003
2.751
- - -
6.14
• 535
.0225
-.0300
.011
2.527
.238
6.16
.583
.0332
-.0313
.010
2.534
.222
6.17
.597
.0476
-.0316
.006
2.583
.167
6.14
.544
.0096
-.0219
.029
2.290
.456
6.16
.592
.0226
-.0256
.026
2.292
.420
6.17
.598
.0372
-.0262
.019
2.365
.353
6.15
.551
-.0024
-.0158
.045
2.093
• 592
6.17
.598
.0147
-.0211
.039
'2.125
.531
6.17
.604
.0258
-.0216
.036
2.130
.514
6.15
• 557
-.0127
-.0113
.059
1.933
.664
6.17
.600
.0095
-.0192
.047
2.030
.581
6.17
.610
.0175
-0197
.047
1.991
.580
*7.17
.629
.0370
-.0549
_ _ _
_ _ _
- - -
“7.18
.651
.0576
-.0483
...
*7.17
.637
.0695
-«73
—
—
7.17
.627
.0393
-.0489
-.001
2.779
- . .
7.18
.671
.0591
-.0432
-.004
2.774
...
7.18
.667
.0702
-.0362
-.003
2.764
- - -
7.17
.630
.0289
-.0394
.01 2
2.526
.241
7.19
.680
.0492
-.0408
.008
2.555
.208
7.18
.672
.0632
-0332
.007
2.578
.176
7.17
.641
.0158
-.0358
.030
2.279
.468
7.19
.685
.0397
-.0345
.024
2.317
.405
7.18
.673
.05*0
-.0269
.018
2.382
.353
7.18
.650
.0049
-.0294
.047
2.089
.600
7.19
.687
.0320
-.0320
.036
2.155
.517
7.19
.678
.0422
-.0230
.035
2.147
.510
7.18
.657
-.0045
-.0265
.059
1.938
.670
7.19
.690
•0259
-.0295
.045
2.045
.578
7.19
.685
.0345
-.0219
.045
2.007
.584
a 8.19
.714
.0488
-.0679
_
_ _ _
_ _ .
*8.19
.705
.0772
-0477
...
*8.19
.695
.0873
-.0343
—
8.19
.717
.0493
-.0548
-.001
2.783
_ _ _
8.20
.733
.0769
-.0366
-.005
2.788
- - -
8.20
.726
.0883
-.0302
-.004
2.776
- - -
8.20
.726
.0406
-.0512
.011
2.551
•236
8.20
.744
.0699
-.0338
.008
2.560
.208
8.20
.739
.0804
-.0333
.007
2.574
.194
8.20
.734
.0282
-.0438
.028
2.299
.458
8.20
.752
.0581
-.0305
.022
2.339
.415
8.20
.746
.0731
-.0296
.018
2.384
.357
8.20
.745
.0172
-.0382
.046
2.101
• 598
8.21
.756
.0517
-.0281
.036
2.163
.520
8.20
.753
.0610
-.0260
.033
2.131
• 523
8.20
.753
.0074
-.0361
.060
1.945
.677
8.21
.761
.0463
-.0260
.045
2.048
.582
8.21
.763
.0566
-.0256
.045
2.012
.578
*9.20
.777
.0686
-.0838
- . -
- - -
- - -
a 9.19
.752
.0989
-.0646
. _ -
...
*9.19
.747
.1083
-.0488
...
—
9.21
.791
.0661
-.0609
0
2.792
...
9.20
.784
.0985
-.0359
-.005
2.794
- —
9.20
.181
.1087
-.0368
-.004
2.792
- - -
9.21
.803
.0566
-.0566
.012
2.547
.255
9.22
.805
.0904
-.0360
.007
2.571
.211
9.21
.802
.1019
-.0355
.006
2.592
.195
9.22
.816
.0430
-.0519
.030
2.282
.475
9.22
.822
.0780
-.0356
.023
2.319
.417
9.22
.816
.0927
-.0329
.018
2.377
.371
9.22
.826
.0338
-.0467
.048
2.092
.604
9.22
.822
.0728
-.0383
.035
2.167
.518
9.22
.825
.0848
-.0285
.033
2.155
.520
9.22
.833
.0252
-.0447
.061
1.945
.676
9.22
.825
.0680
-.0392
.045
2.048
.582
9.22
.834
.0783
-.0299
.044
2.016
.584
a 10.21
.833
.0925
-.0939
*10.20
.800
.1230
-.0915
...
*10.19
.781
.1314
-.0840
—
10.22
.857 1
.0921
-.0679
-.001
2.806
- . -
10.21
.832
.1277
-.0447
-.006
2.800
- —
10.21
.829
.1335
-.0432
-.005
2.802
- - -
10.23
.866
.0787
-.0622
.013
2.534
.282
10.22
..849
.1143
-.0449
.007
2.571
.222
10.22
.847
.1312
-.0410
.005
2.599
.198
10.23
.880
.0677
-.0515
.029
2.294
.472
10.23
’.867
.1061
-.0431
.021
2.337
.409
10.23
.872
.1209
-.0349
.017
2.381
• 375
10.24
.890
.0567
-.0458
.047
2.089
.614
10.23
.874
.0995
-.0394
.033
2.182
.516
10.24
.887
.1097
-.0304
.034
2.161
.518
10.24
.900 .
.0494
-.0403
.059
1.956
•679
10.23
.880
.0927
-.0418
.044
2.056
.587
10.23
.897
.1020
-0363
.044
2.035
.587
“Props off. \NACA
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
TABLE IV.- LONGITUDINAL CHARACTERISTICS OF A FOUR-ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 40° OF SWEEPBACK AND AN ASPECT RATIO OF 10; TAIL HEIGHT = 0 b/2, it = -k°,
P = 51°, R = 1,000,000 - Concluded
(b) M = 0.86, 0.90
I
ro
NACA RM A53J23 CONFIDENTIAL
confide:
TABLE V.- LONGITUDINAL CHARACTERISTICS
A WING WITH 4o° OF SWEEPBACK AND AN
p = 51°, R = 1,000,000
(a)
OF A FOUR -ENGINE TRACTOR
ASPECT RATIO OF 10; TAIL
M = 0.70, 0.80, 0.83
AIRPLANE
HEIGHT =
CONFIGURATION HAVING
0 b/2, it = -6°,
$
I
I
4 *
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
TABLE V.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 1*0° OF SWEEPBACK AND AN ASPECT RATIO OF 10; TAIL HEIGHT = 0 b/2, i t = -6°,
P ■ 51°, R = 1,000,000 - Concluded
(b) M * 0.86, 0.90
M, 0.86
M, 0.90
a
c L
cx
Cm
T CdV
Jav.
C Pav
a
Cl
c x
c«
Tc a v.
J av
C Pav.
2.03
0.142
0.0299
0.1203
_ _ .
2.03
0.140
0.0411
0.1243
2.03
• 139
•0354
.0900
-0.003
2.731
- _ _
2.03
.144
.0480
.0710
-0.005
2.711
_
2.03
.130
.0260
.1009
.006
2.547
0.182
2.03
.145
.0362
.0877
.005
2.486
0.184
2.03
.129
.0127
.1145
.021
2.281
.380
2.03
• 143
.0230
.1098
.018
2.225
.347
2.03
.128
.0031
.1277
.034
2.095
.486
2.03
.141
.0127
.1264
.027
2.025
.430
2.03
.126
-.0100
.1431
.047
1.874
•554
2.03
•138
.0063
.1364
.035
1.861
.465
3-07
.261
.0314
.0922
...
- - -
3.06
.229
.0454
.1050
3.07
.261
.0356
.0637
-.003
2.740
— -
3.07
•257
.0483
.0500
-.005
2.727
3.07
.259
.0270
.0753
.005
2.559
.179
3.07
.262
•0375
.0687
.007
2.481
.199
3.07
.260
.0156
.0900
.020
2.307
• 373
3-07
.261
.0302
.0795
.018
2.244
•345
3-07
.260
.0037
.1047
.034
2.081
.499
3.07
.263
.0201
.0887
.027
2.044
.425
3-07
.260
-.0080
.1176
.047
1.891
• 567
3.07
.268
.0120
•0955
.036
1.879
.466
4.10
• 371
.0370
.0702
...
4.08
.327
.0527
.0797
4.10
• 378
.0418
.0432
-.003
2.744
- - -
4.09
.347
.0567
• 0332
-.005
2.727
_ . .
4.10
.380
.0334
.0559
.005
2.558
.178
4.09
.347
.0479
.0522
.007
2.470
.204
4.10
• 383
.0251
.0687
.020
2.304
.380
4.09
•356
.0366
.0622
.019
2.235
•358
4.11
.386
.0089
.0783
•033
2.093
.512
4.10
.359
.0288
.0678
.027
2.045
.429
4.11
• 391
-.0004
.0832
.047
1.901
• 573
4.10
.360
.0242
.0712
• 035
1.888
.465
5.12
.461
.0492
.0483
5-11
.420
.0627
.0609
5.13
.480
.0528
.0296
-.003
2.749
- - _
5.H
.431
.0676
• 0323
-.004
2.734
_ _ _
5.13
.479
.0449
.0400
.006
2.566
.179
5.12
.437
.0569
• 0453
.008
2.479
.227
5-13
.483
.0320
.0513
.020
2.317
.381
5-12
.441
.0487
.0501
.019
2 .244
• 362
5.14
.486
.0229
.0558
.032
2.121
.498
5-12
.442
.0437
.0539
.028
2.050
.430
5.14
.493
.0103
.0592
.046
1.913
• 583
5.12
.449
•0353
• 0556
.035
1.899
.469
6.14
•533
.0644
.0402
...
6.13
.489
.0795
.0478
6.15
• 558
.0671
.0227
-.004
2.751
_ _ _
6.13
•512
.0792
.0286
-.004
2.745
_
6.15
.562
.0578
.0313
.005
2.578
.180
6.13
.516
.0722
•0351
.009
2.469
239
6.15
• 564
.0471
.0387
.020
2.324
.382
6.14
•525
.0629
•0376
.019
2.242
• 390
6.16
• 572
.0363
.0435
.034
2.104
.514
6.14
• 538
.0548
.0349
.029
2.035
.462
6.16
• 579
.0260
.0461
.047
1.919
.580
6.14
.543
.0501
.0354
• 035
1.912
.494
7.16
.604
.0795
.0315
...
_ _ _
- - -
7.14
.566
.0912
.0309
7.14
.632
.0826
.0180
-.004
2.763
7.15
.588
.0968
.0147
-.004
2.748
7.17
.636
.0741
.0292
.006
2.580
.185
7.15
•595
.0881
.0231
.008
2.489
.240
7.17
.638
.0629
.0360
.020
2.325
• 391
7.16
.605
.0785
.0248
.019
2.248
.392
7.18
.645
.0546
.0388
.032
2.131
.503
7.16
.613
.0722
.0254
.028
2.053
.464
7.18
•653
.0438
.0423
.045
1.943
• 583
7.16
.617
.0667
.0263
.034
1.931
.496
8.17
.666
.0973
.0175
...
8.16
.638
.1115
.0071
8.18
.692
.1003
.0188
-•005
2.775
— -
8.17
.650
.1167
.0060
-.004
2.765
- - -
8.!9
.707
.0922
.0238
.006
2.579
.200
8.17
.674
.1087
.0116
.008
2.489
.248
8.19
.714
.0819
.0303
.021
2.323
•395
8.18
.682
.0997
.0161
.019
2.259
.405
8.19
.722
.0730
.0343
.033
2.127
• 512
8.18
.686
.0914
.0169
.028
2.080
.469
8.20
• 730
.0649
.0362
.045
1.956
.583
8.18
.693
.0862
.0167
• 035
1.940
.501
9.18
.724
.1170
.0005
- - -
9.18
.699
.1369
-.0136
9.19
•752
.1219
.0128
-.005
2.787
...
9.18
.722
.1375
-.0002
-.005
2.779
_ _ _
9.20
.773
.1139
.0175
.006
2.585
.198
9.19
.740
•1373
.0021
.003
2.612
.167
9-20
.782
.1057
.0226
.021
2.331
•389
9.19
• 751
.1217
.0048
.017
2.309
.381
9.21
• 791
.0938
.0251
.033
2.131
.515
9.20
• 758
.1148
.0074
.026
2.132
.464
9.21
.801
.0878
.0304
.045
1.977
•586
9.20
.765
.IO85
.0073
•035
1.954
-517
10.19
• 779
.1399
-.0100
IO.19
.762
.1613
-.0277
10.21
.807
.1468
.0107
-.006
2.798
- - -
10.20
• 791
.1615
-.0094
-.005
2-795
10.21
.825
.1364
.0191
.006
2.601
.202
10.21
.821
.1603
-.0079
.006
2.564
.203
10.22
.844
.1286
.0197
.021
2.341
.400
10.21
.826
.1538
-.0070
.017
2.321
.385
10.22
.855
.1225
.0233
•033
2.148
.510
10.21
.832
.1448
-.0086
.026
2.126
.471
10.22
.862
.1139
.0286
.045
1.978
• 587
10.22
.838
• 1396
..OO56
.034
1.991
• 514
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
TABLE VI.
A WING
- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
WITH 40° OF SWEEPBACK AND AN ASPECT RATIO OF 10; TAIL OFF, 8 = 51° > R * 1,000,000
(a) M = 0.70, 0.80, 0.83
8
hf —
T c a v
Cp av
-0.004
2.733
.007
2.542
0.181
.028
2.204
.444
.037
2.072
•514
.050
1.895
• 586
-.004
2.737
_ _ _
.007
2.543
• 191
.024
2.257
.411
.039
2.052
.531
.050
1.909
.589
1 -.003
2.735
• .007
2.544
.190
1 .024
2.269
.413
l .038
2.075
• 531
.049
1.926
.597
1
k -.003
2.736
„
) .007
2.548
.190
.024
2.271
.420
.038
2.087
.531
! .049
1.934
.599
> -.003
2.749
'
.008
2.551
.i9e
> .025
2.272
.428
k .040
2.075
.543
) .049
1.946
.597
L
k -.004
2.757
—
) .007
2.560
.199
J .025
2.267
.428
3 .040
2.078
.550
5 .049
1.959
.603
> ...
> -.004
2.771
5 .007
2.565
.200
3 .024
2.276
.435
2 .039
2.087
• 550
1 .048
1.964
.601
1 - - -
7 -.004
2.780
—
0 .006
2.572
.202
4 .024
2.281
.436
2 .039
2.088
.551
3 .047
1.964
.604
2 - - -
1 -.005
2.796
—
2 .006
2.582
.213
2 .024
2.283
.443
1 .038
2.103
.542
3 .047
1.976
.602
a
CL
Cx '
c. '
*2.04
0.169
0.0201
-0.0466
2.04
.159
.0233
-.0693
-0.003
2.04
.154
.0111
-.0587
.on
2.04
.152
.0012
-.0498
.023
2.04
.150
-.0089
-.0422
.037
2.04
.150
-.0251
-.0338
.058
*3.07
.262
.0214
-.0431
...
3.06
.253
.0238
-.0610
-.002
3.06
.252
.0136
-.0541
.009
3.06
.252
.0008
-.0421
.025
3.06
.252
-.0117
-.0341
.042
3.06
.252
-.0246
-.0287
.057
a 4.09
.353
.0222
-.0425
4.09
.346
.0254
-.0521
-.002
4.09
.346
.0151
-.0452
.on
4.09
.347
.0029
-.0359
.025
4.09
.350
-.0069
-.0263
.041
4.09
.352
-.0223
-.0200
.057
a 5.12
.442
.0258
-.0363
...
5.12
.437
.0281
-.0438
-.002
5.12
.440
.0181
-0358
.010
5.12
.444
.0059
-.0261
.026
5.12
.449
-.0067
-.0173
.042
5.12
.453
-.0190
-.0110
.057
*6.14
• 533
.0295
-.0337
6.14
• 530
.0319
-.0342
-.001
6.14
• 532
.0216
-.0262
.011
6.14
• 537
.0094
-.0153
.027
6.14
.543
-.0025
-.0076
.043
6.15
.549
-.0138
-.0014
.058
*7.16
.617
.0361
-.0287
7.16
.617
.0375
-.0245
-.001
7.16
.620
.0268
-.0133
.012
7.17
.627
.0171
-.0058
.026
7.17
.635
.0049
.0029
.043
7.17
.642
-.0051
.0092
.058
“8.19
.694
.0473
-.0163
8.19
.701
.0468
-.0097
-.001
8.19
.706
.0370
-.0006
.012
8.19
.711
.0273
.0066
.026
8.19
.719
.0166
.0147
.042
8.19
.727
.0068
.0212
.058
“9.19
.748
.0659
-.0097
9.20
.768
.0630
.0060
0
9.20
.778
.0517
.0151
.014
9.21
.787
.0424
.0212
.027
9.21
.797
.0318
.0290
.045
9.21
.805
.0228
.0333
.058
“10.20
.796
.0892
.0083
10.21
.827
.0857
.0286
-.001
10.22
.835
.0746
.0340
.014
10.22
.844
.0654
.0387
.026
10.22
.855
.0540
.0462
.045
10.23
.865
.0458
.0533
.058
a
-0.0478
_ _ _
_ _ _
“2.05
-.0716
-0.004
2.742
- - -
2.05
-.0671
.001
2.623
0.117
2.04
-.0585
.014
2.407
.310
2.04
-.0471
.031
2.170
.501
2.04
-.0407
.049
1.950
.599
2.04
-.0473
“3.08
-.0656
-.004
2.740
- - -
3.08
-.0577
.005
2.572
.170
3.08
-.0478
.021
2.321
.381
3.08
-.0391
.039
2.079
.543
3.08
-.0357
.048
1.969
.596
3.08
-.0440
“4.11
-.0576
-.004
2.743
• - -
4.11
-.0496
.005
2.580
.164
4.11
-.0403
.020
2.334
.378
4.11
-.0308
.037
2.107
.533
4.11
-.0267
.048
1.978
.600
4.11
-.0375
_ _ _
_ _ -
“5.14
-.0477
-.003
2.744
— -
5.14
-.0408
.006
2.583
.165
5.14
-.031 1
.021
2.336
.378
5.14
-.0238
.038
2.108
• 530
5.14
-.0197
.048
1.984
.601
5.14
-.0379
_ _ _
a 6.l6
-.0403
-.003
2.749
—
6.16
-.0324
.006
2.587
.170
6.16
-.0236
.021
2.338
.381
6.16
-.0155
.038
2 .111
.542
6.17
-.0129
.048
1.990
.599
6.17
-.0253
_ _ _
_ _ _
“7.17
-.0268
-.004
2.755
- - -
7.18
-.0215
.006
2.589
.174
7.18
-.0116
.022
2.323
.406
7.18
-.0068
.038
2. no
.540
7.18
-.0031
.047
1.992
.600
7.19
-.0097
...
“8.18
-.0028
-.005
2.773
- - -
8.19
.0016
.006
2.593
.185
8.19
.0103
.020
2.352
.385
8.20
.0153
.038
2.115
.546
8.20
.0182
.047
2.005
.602
8.20
-.0059
"9.19
.0132
-.005
2.784
- —
9.20
.0184
.005
2.598
.190
9.21
.0254
.020
2.346
.398
9.21
.0261
.037
2.127
.547
9.21
.0262
.047
2.006
.606
9.22
.0005
_ _ _
- - -
“10.18
.0271
-.006
2.796
-
10.20
.0285
.005
2.600
.199
10.21
.0373
.020
2.348
.409
10.21
.0445
.038
2.125
.554
10.22
.0433
.046
2.028
.607
10.22
2.783
2.511
2.325
2.176
1.950
2.780
2.541
2.320
2.127
1.953
0.257
.414
• 536
.657
2.782
2.531
2.330
2.144
1.958
2.781
2.537
2.334
2.137
1.956
2.781
2.527
2.324
2.126
1.955
2.787
2.527
2.335
2.130
1.964
2.788
2.539
2.342
2.144
1.969
2.799
2.536
2.329
2.229
1.980
2.819
2.528
2.337
2.130
1.980
•253
.425
• 579
.661
.247
.422
•5 7 2
.663
.266
.438
• 583
.663
.283
.438
.588
.658
“2.05
2.04
2.04
2.04
2.04
2.04
‘3.08
3.07
3.07
3.07
3.08
3.08
“4.10
4.10
4.10
4.10
4.11
4.11
“5-13
5-13
5.13
5.14
5.14
5.14
“6.16
6.16
6.16
6.16
6.16
6.17
“7.18
7.18
7.18
7.18
7.19
7.19
“8. 18
8.19
8.20
8.20
8.20
8.20
“9.19
9.20
9.20
9.21
9.21
9.21
*10.19
10.20
10.21
10.22
10.22
10.22
0.176
.168
.166
.164
.164
.164
.279
.272
.274
.274
.276
.277
.379
.377
.377
.380
• 385
.386
.484
.483
.484
.490
.495
.496
.573
.580
.583
.588
.593
.596
.646
.664
.668
.673
.676
.680
.690
.720
.729
.736
.740
.748
.731
.767
.784
.794
.796
.798
.771
.804
.815
.836
.849
.853
0.0231
.0266 ,
.0213
.0108
-.0030
-.0170
.0238
.0271
.0195
.0071
-.0079
-.0148
.0263
.0297
.0223
.0099
-.0035
.0120
.0319
.0345
.0272
.0150
.0023
.0061
.0425
.0439
.0355
.0246
.0113
.0049
.0570
.0575
.0494
.0379
.0265
.0198
.0751
.0758
.0667
.0579
.0452
.0389
.0951
•0953
.0879
.0773
.0667
.0610
.II85
.1177
.1102
.1013
.0909
.0847
0.182
.176
.172
.171
.170
.170
.289
.286
.283
.286
.288
.290
• 399
.397
.395
.400
.402
.407
.497
.499
.500
.509
• 511
• 515
• 573
.587
• 592
.594
.598
.611
.635
.659
.665
.667
.673
.712
.727
.735
.744
.753
.732
.765
.783
.802
.806
.815
.755
.804
.810
.832
.837
.839
0.0251
.0291
.0203
.0028
.0052
.0167
.0259
.0299
.0203
.0063
-.0054
-.0140
.0297
.0338
.0237
.0105
-.0006
-.0107
.0387
.0407
.0318
.0180
.0073
.0018
.0522
.0527
.0434
.0299
.0191
.0119
.0675-
.0696
.0594
.0466
.0361
.0292
.0856
.0881
.0784
.0656
.0549
.0487
.1053
.1077
.1000
.0881
.0789
.0716
.1267
.1291
.1203
.1101
.1023
.0952
•0.0449
-.0729
-.0660
-.0528
-.0462
-.0400
-.0467
-.0666
“Props off.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
CJl
O
TABLE VI.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 1*0° OF SWEEPBACK AND AN ASPECT RATIO OF 10) TAIL OFF, p * 51°, R = 1,000,000 -
Concluded
(L) M » 0.86, 0.90
M, 0.86
M, 0.90
a
cl
Cx
Cm
T Cav
J av
C Pav
a
cl
Cx
Cm
T cav
Jav
C Pav
•"2.06
0.196
0.0282
-0.0439
—
—
®2.06
0.197
0.0368
-0.0441
2.05
.182
.0305
-.0734
-0.005
2.743
2.06
.198
.0401
-.0849
-0.005
2.708
- . _
2.05
.183
.0224
-.0639
.006
2.547
0.178
2.05
.194
.0332
-.0759
.003
2.542
0.187
2.05
.183
.0140
-.0576
.017
2.353
• 325
2.05
.194
.0221
-.0657
.015
2.286
• 321
2.05
.182
.0038
-.0474
.029
2.148
.451
2.05
.193
.0091
-.0543
.027
2.034
.432
2.05
.181
-.0066
-.0417
.041
1.964
.560
2.05
.192
.0034
-.0505
•035
1.878
.468
a 3.07
.305
.0304
-.0474
a 3.08
.286
.0413
-.0478
_ _ _
3.08
.297
.0324
-.0707
-.005
2.750
• - -
3.08
.296
.0474
-.0895
-.005
2.716
3.08
.299
.0249
-.0633
.006
2.557
.176
3.08
.300
.0382
-.0776
.003
2.542
.158
3.08
.301
.0160
-.0568
.017
2.360
.329
3.09
.306
.0266
-.0715
.015
2.291
.332
3.08
• 303
.0059
-.0474
.029
2.162
.458
. 3.09
.306
.0197
-.0665
.026
2.067
.426
3.08
.302
-.0053
-.0417
.042
1.975
.539
3.09
.309
.0091
-.0616
.035
1.891
.473
*4.11
.406
• 0371
-.0484
- - -
_ - -
a 4.10
.373
.0503
-0539
-
4.10
.411
.0384
-.0686
-.004
2.748
- - -
4.11
.386
.0566
-.0849
-.005
2.726
4.12
.413
.0311
-.0614
.006
2.555
.184
4.11
.387
.0473
-.0734
.004
2.549
.160
4.12
.418
.0219
-.0528
.017
2.362
.343
4.11
• 393
.0360
-.0682
.015
2.303
• 333
4.12
.422
.0108
-.0450
.029
2.160
.478
4.11
.400
.0253
-.0618
.027
2.056
.436
4.12
.425
.0010
-.0401
.041
1.984
• 551
4.11
.401
.0199
-.0593
.035
1.897
.479
a 5.l4
.492
.0485
-.0456
a 5.12
.451
.0632
-.0494
- - _
5.14
.505
.0486
-.0632
-.004
2.754
— -
5.13.
.465
.0667
-.0684
-.004
2.734
5.14
.506
•04l4
-.0547
.006
2.560
.186
5.12
.463
.0596
-.0626
.004
2.558
-.163
5.14
.510
.0318
-.0477
.018
2.355
.355
5.13
.473
.0485
-.0569
.015
2.310
• 341
5.14
• 512
.0230
-.0428
.030
2.159
.477
5.i3
.481
.0374
-.0506
.027
2.061
.452
5.14
.517
.0128
-.0380
.042
1.982
.554
5.14
.485
.0312
-.0484
.034
1.927
.480
a 6.l 5
• 562
.0628
-.0397
- - -
*6.14
.521
.0761
-.0433
6.16
• 583
.0625
-.0485
-.004
2.761
-
6.14
.528
.0821
-.0577
-.004
2.749
6.16
.586
.0562
-.0409
.006
2.567
.187
6.14
• 535
.0745
-.0493
.005
2.555
• 173
6.16
.587
.0476
-.0361
.018
2.368
.349
6.15
.545
.0643
-.0427
.016
2.320
.345
6.16
•593
.0373
-.0297
.030
2.166
.480
6.15
.555
• 0532
-.0374
.028
2.062
• 453
6.17
• 599
.0276
-.0252
.042
1.990
• 559
6.15
.561
.0495
-.0348
.035
1.923
.490
“7.16
.623
.0784
-.0278
®7.15
.584
.0934
-.0337
7.18
.651
.0800
-.0315
-.004
2.764
- - -
7.16
.607
.0976
-.0435
-.004
2.755
7.18
.650
• 0737
-.0258
.006
2.571
.191
7.16
.608
.0924
-.0380
.005
2.565
.175
7.18
.653
.0645
-.0197
.017
2.375
.353
7.16
.617
.0807
-.0312
.017
2.310
.356
7.18
.659
.0540
-.0136
.029
2.180
.482
7.16
.624
.0743
-.0279
.025
2.126
.445
7.18
.665
.0456
-.0112
.042
1.992
.561
7.17
.630
.0664
-.0250
.034
1.949
.496
*8.18
.675
.0967
-.0177
- - -
*8.17
.649
.1101
-.0268
8.19
.704
.0966
-.0137
-.004
2.782
—
8.17
.664
.1161
-.0291
-.004
2.767
_ _ _
8.19
.716
.0919
-.0091
.007
2.578
.197
8.18
.676
.1119
-.0241
.005
2.566
.181
8.19
.720
.0834
-.0025
.018
2.370
.364
8.18
.683
.1013
-.0195
.017
2.324
.354
8.19
.727
.0742
.0020
.031
2.172
.488
8.18
.691
.0956
-.0154
.025
2.130
.448
8.20
•735
.0660
.0064
.042
2.004
• 569
8.19
.697
.0869
-.0124
.034
1.956
.503
*9.19
.725
.1169
-.0074
- - -
- - -
*9.18
.698
.1322
-.0162
9.19
.754
• 1175
.0014
-.005
2.792
—
9.18
.721
.1387
-.0123
-.005
2.779
- - -
9.20
.773
.1133
.0057
.006
2.589
.195
9.19
.737
.1332
-.0119
.005
2.578
.182
9.20
.782
.1034
.0126
.018
2.380
.362
9.19
.748
.1281
-.0042
.017
2.328
.364
9.21
.791
.0969
.0172
.031
2.175
.498
9.19
.754
.1156
-.0007
.026
2.129
.465
9.21
.798
.0879
.0216
.042
2.013
• 570
9.20
.759
.1119
.0023
.034
1.963
.499
*10.18
.752
.1379
.0007
- - -
*10.18
.750
.1597
-.0008
- - -
_ _ _
- - -
10.20
.800
.1415
.0202
-.005
2.812
- - -
10.20
.785
.1659
.0055
-.005
2.802
10.21
.819
.1354
.0266
.007
2.590
.202
10.21
.807
.1548
.0081
.006
2.585
.200
10.22
.837
.1292
.0339
.019
2.380
.376
10.21
.816
.1508
.0128
.018
2.324
.378
10.22
.847
.1227
.0380
.030
2.196
.488
10.21
.819
.1412
.0167
.026
2.145
.468
10.22
.855
.1121
.0415
.042
2.033
.566
10.21
.824
.1388
.0216
.034
1.986
.516
U)
00
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
TABLE VII.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING *r-
A WING WITH 40° OF SWEEPRACK AND AN ASPECT RATIO OF 10; TAIL HEIGHT = 0 t>/2, it = -V ,
0 « 51°, R = 2,000,000
M = 0.70, 0.80, 0.90
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
TABLE VIII.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 40° OF SWEEPBACK AND AN ASPECT RATIO OF 10; TAIL OFF, p = 51 °, R = 2,000,000
M = 0.70, o. 8 o, 0.90
M, 0.70
M, 0.80
M, 0.90
a
CL
cx
Cm
T Cav
J av
c Pav
a
c L
C X
Cm
T Cav
Jav
c Pav
a
C L
Cx
Cm
T Cav
Jav
C Pav
*2.04
0.161
0.0179
-0.0452
—
a 2.0*
0.167
0.0207
-0.0478
_ _ _
a 2.06
0.208
0.0372
-0.0637
2.04
.154
.0209
-.0676
-0.003
2.770
—
2.0*
.158
.02*2
-.0711
-0.004
2.7*4
_ _ _
2.05
.188
.0361
-.0803
-0.005
2.726
_ _
2.04
.152
.0143
-.0613
.006
2.620
0.160
2.04
.154
.0198
-.0677
.001
2.648
0.103
2.05
.186
.032*
-.0763
-.001
2.628
0.090
2.04
.151
.0091
-.0574
.012
2.522
.260
2.04
.153
.0131
-.0616
.009
2.503
.2*2
2.05
.183
.0272
-.0702
.005
2.508
.197
2.04
.150
.0048
-.0537
.017
2.435
.3*2
2.04
.153
.0072
-.0572
.015
2.393
.3*2
2.05
.182
.0208
-.0639
.012
2.368
.292
2,04
.149
-.0023
-.0487
.027
2.296
.446
2.0*
.153
.0030
-.0544
.020
2.323
.400
2.05
.181
.0181
-.0604
.016
2.276
.3*3
*3.07
.255
.0187
-.0426
—
a 3.07
.269
.0211
-.0*7*
_ _ _
_ _ _
a 3.o8
.283
.0374
-.0568
3.06
.248
.0215
-.0580
-.003
2.769
- - -
3.07
.262
.0246
-.0631
-.004
2.7*9
_ _ _
3.08
.297
.0*02
-.0878
-.005
2.727
3.06
.245
.0152
-.0522
.005
2.631
.153
3.07
.261
.0212
-.0593
.001
2.660
.091
3.08
.297
.0364
-.0832
-.001
2.636
.089
3.06
.2*»6
.0107
-.0491
.011
2.536
.2*3
3.07
.262
.0136
-.0527
.009
2.511
.233
3.08
.297
.0311
-.0766
.005
2.512
.198
3.06
.245
.oo4i
-.0443
.019
2.420
.359
3.07
.263
.0092
-.0487
.015
2.415
.325
3.08
.298
.025*
-.0728
.011
2.377
.291
3.06
.246
-.0019
-.0408
.026
2.319
.448
3.07
.264
.0037
-.0*57
.021
2.316
.407
3.08
.299
.0212
-.0683
.016
2.292
.3*7
a 4.09
.345
.0207
-.0389
a 4.10
.369
.023*
-.0*23
_ _ _
_ _ _
a 4.10
.376
.0460
-.0630
4.09
.339
.0231
-.01*86
-.002
2.771
- - -
4.10
.365
.0268
-.0532
-.004
2.753
_ _ _
4.11
.402
.0486
-.0923
-.004
2.7*3
4.09
.340
.0174
-.0433
.005
2.632
.138
4.10
.365
.0234
-.0486
0
2.671
.082
4.11
.401
.0448
-.0897
-.001
2.665
.07*
4.09
.340
.0126
-.0408
.011
2.541
.234
4.10
.366
.0156
-.0*19
.009
2.509
.246
4.11
.402
.0407
-.0855
.005
2.535
.183
4.09
.3*1
.0061
-.0362
.019
2.432
.352
4.10
.369
.0113
-.0377
.015
2.416
.330
4.11
.403
.0353
-.0812
.010
2.426
.267
4.09
.3*3
-.0007
-.0307
.027
2.321
.460
4.10
.368
.0063
-.0362
.020
2.332
.399
4.11
.407
.0290
-.0776
.016
2.305
.336
*5.12
.435
.0235
-.0337
—
a 5.13
.*73
.0276
-.0390
_ _ _
a 5.12
.443
.0639
-.06*3
5.11
.432
.0258
-.0387
-.002
2.769
- - -
5.13
.472
.0310
-.0463
-.004
2.7*8
_ _ _
5.1*
.486
.0631
-.0881
-.004
2.7*9
_
5.U
.432
.0202
-.0332
.005
2.636
.132
5.13
.*72
.0271
-.0*16
0
2.665
.093
5.14
.487
.0552
-.0834
0
2.662
.088
5.11
.434
.0156
-.0305
.011
2.544
.228
5.13
.476
.0206
-.0358
.009
2.519
.327
5.14
.485
.0506
-.07*4
.005
2.537
.196
5.12
.436
.0088
-.0245
.019
2.436
.357
5.13
.*77
.0157
-.0317
.014
2.423
.328
5.13
.484
.0463
-.07*1
.010
2.423
.281
5.12
.439
.0025
-.0199
.027
2.329
.*55
5.13
.*78
.0106
-.0286
.020
2.327
.405
5.13
.482
.0*28
-.0717
.016
2.319
.3*5
**6.14
.524
.0270
-.0281
—
a 6.l6
• 571
.0366
-.0350
_ _ _
_ _ _
_ _ _
a 6.13
.512
.0768
-.0579
6.14
.522
.0292
-.0286
-.002
2.771
- - -
6.16
.576
.0388
-.0*05
-.004
2.755
_ . _
6.15
.551
.0764
-.0704
•*.004
2.756
_ _ _
6.14
.523
.0257
-.0244
.003
2.673
.13*
6.16
.575
.0352
-.0372
0
2.676
.083
6.15
.554
.0713
-.0683
0
2.666
.091
6.14
.524
.0192
-.0217
.011
2.541
.232
6.16
.578
.0287
-.0303
.006
2.533
.231
6.15
.55*
.0654
-.0632
.005
2.5*2
.200
6.14
• 528
.0132
-.0151
.019
2.445
•35e
6.16
.581
.0237
-.0259
.015
2.419
.362
6.15
.553
.0610
-.0593
.010
2.438
.286
6.14
.531
.0065
-.0103
.028
2.332
.*59
6.16
.582
.0197
-.0219
.020
2.333
.409
6.15
.558
.05*0
-.0565
.016
2.329
.353
“7.16
.611
.0325
-.0229
—
“7.18
.648
.0500
-.0299
_ _ _
_ _ _
*7.15
.582
.0919
-.0*98
7.16
.612
.0345
-.0198
-.002
2.773
- —
7.18
.668
.05U
-.0304
-.004
2.765
7.16
.614
.0923
-.0530
-.004
2.776
_ _ _
7.16
.613
.0292
-.0145
.005
2.642
.136
7.18
.670
.0*77
-.0272
.001
2.684
.091
7.16
.617
.0864
-.0505
0
2.680
.090
7.16
.615
.0243
-.0114
.on
2.5*2
.248
7.18
.672
.0*05
-.0213
.009
2.524
.246
7.16
.614
.0815
-.0465
.005
2.56*
.187
7.16
.619
.0191
-.0059
.018
2.443
.350
7.18
.672
.0351
-.0184
.016
2.407
.350
7.16
.615
.0781
-.0*26
.011
2.432
.278
7.16
.622
.0124
-.0010
.027
2.333
.*59
7.18
.672
.0323
-.0159
.021
2.338
.406
7.16
.620
.07*3
-.0399
.016
2.337
.351
a 8.l8
.692
.0417
-.0147
a 8.l9
.700
.0679
-.0160
- - «
...
**8.17
.6*9
.1092
-.0399
8.19
.700
.0430
-.0086
-.002
2.775
- - -
8.20
.732
.0678
-.0099
-.004
2.778
_ - _
8.18
.680
.1112
-.0388
-.00*
2.784
_
8.19
.703
.0375
-.0033
.004
2.648
.149
8.20
.732
.0641
-.0079
0
2.696
.091
8.18
.683
.1053
-.0365
0
2.687
.095
8.19
.705
.0327
-.0014
.011
2.5*5
.257
8.20
.739
.0587
-.0038
.010
2.529
.250
8.18
.682
.1010
-.0323
.005
2.566
.205
8.19
.709
.0284
.0015
.017
2.451
• 352
8.20
.7*2
.0525
0
.017
2.411
.360
8.18
.687
.0954
-.0283
.010
2.465
.285
8.19
.712
.0227
.0030
.025
2.338
.45*
8.20
.745
.0*99
.0018
.021
2.3*8
.414
8.18
.687
.0906
-0259
.016
2.338
.363
* 9.19
.750
.0597
-.0103
* 9.19
.7*3
.0862
-.0024
_ _ _
_ . _
_ _ _
^.18
.700
.1346
-.0287
9.20
.778
.0568
• 004l
-.002
2.787
—
9.21
.784
.0882
.OU‘5
-.004
2.786
_ , _
9.19
.7*1
.13*3
-.0238
-.005
2.792
_ _ _
9.20
.783
.0503
.0091
.006
2.638
.170
9.21
.788
.0829
.0127
.002
2.677
.139
9.19
.7*3
.1271
-.0202
0
2.688
.102
9.21
.788
.0463
.0127
.012
2.5*3
.270
9.21
.798
.0783
.017*
.010
2.533
.259
9.19
.7*6
.1211
-.0164
.005
2.569
.211
9.21
.788
.0424
.0160
.017
2.45*
.356
9.18
.801
.0719
.0205
.017
2.421
.358
9.19
.7*9
.1184
-.0125
.010
2.462
.299
9.21
.793
.0372
.0204
.025
2.3*5
.*53
9.21
.807
.0704
.02*1
.021
2.356
.409
9.19
.7*9
.1114
-.0094
.016
2.359
.364
a 10.21
.806
.0803
-.0007
a 10.19
.782
.1091
-.00*5
_ _ _
_ _ _
a lo.i9
.765
.1581
-.0196
10.22
.840
.0769
.0105
-.003
2.808
- - -
10.21
.823
.1117
.0278
-.004
2.793
_ _ _
10.21
.806
.1573
-.0066
-.005
2.810
10.22
.841
.0715
.0257
.005
2.651
.171
10.21
.828
.1070
.0304
.001
2.693
.113
10.21
.805
.1501
-.0002
0
2.698
.1 12
10.22
.845
.0678
.0307
.oil
2.55*
.269
10.22
.838
.1007
.0304
.009
2.533
.267
10.21
.806
.1441
.0026
.005
2.576
.215
10.22
.851
.0634
.0334
.018
2.454
.361
10.22
.8*5
.0965
.0327
.015
2.447
.350
10.21
.808
.1424
.0052
.010
2.478
.296
10.22
.857
.0582
.0377
.025
2.3*8
.*53
10.22
.851
.0952
.0361
.020
2.367
.415
10.21
.812
.1378
.0071
.016
2.358
.371
a Propa off.
U)
U1
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
TABLE IX.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 40° OF SWEEPBACK AND AN ASPECT RATIO OF 10; TAIL HEIGHT = 0 b/2, it = -4°,
3 « iH 0 , R * 2,000,000
M = 0.60, 0.70, 0.80
M, 0.60
M, 0.70
M, 0.00
a
CL
Cx
c*
T r
c av
Jav
CPav
a
c L
C X
c»
T Cav
Jav
c Pav
a
c L
cx
c«
TCav
Jav
Cp
^av
*2.04
0.159
0.0174
-0.0429
“2.04
0.161
0.0179
-0.0452
- . _
“2.04
0.167
0.0207
-0.0478
2.03
• 123
.0220
.0306
-0.003
1.933
- - -
2.03
.127
.0236
.0276
-0.005
1.940
- - -
2.03
.138
.0266
.0240-
-0.006
1.949
- - -
2.03
.123
.0155
.0340
.004
1.872
0.055
2.03
.125
.0159
.0340
.006
1,866
0.067
2.03
.134
.0208
.0303
.001
1.893
0.047
2.03
.121
.0042
.0423
.019
1.774
.141
2.03
.124
.0072
.0414
.017
1.787
• 131
2.03
.133
.0120
.0373
.013
1.798
.116
2.03
• U9
-.0089
.0516
.034
1.677
.220
2.03
.122
-.0013
.0480
.028
1.715
.186
2.03
.132
.0037
.0446
.022
1.727
.172
2.03
.117
-.0210
.0594
.049
1.599
.280
2.03
.120
-.0117
.0550
.039
1.635
.245
2.03
.131
-.0034
.0494
.031
1.668
.212
a 3.06
.247
.0182
-.0383
- - -
“3-07
•255
.0187
-.0426
- - -
- - -
“3.07
.269
.0211
-.0474
—
3.05
.219
.0224
.0157
-.003
1.931
- - ^
3.06
.228
.0241
.0156
-.004
1.939
- - -
3.06
.246
.0271
.0109
-.005
1.947
- - -
3.05
.220
.0117
.0235
.011
1.830
.088
3.06
.228
.0160
.0219
.006
1.862
.069
3.06
.245
.0238
.0144
-.002
1.917
.027
3.05
.220
.0052
.0277
.018
1.777
.134
3.06
.228
.0074
.0275
.016
1.787
.132
3.06
.246
.0131
•0233
.011
1.011
.115
3.05
.220
-.0090
.0351
.035
1.678
.221
3.06
.229
-.0000
.0331
.026
1.717
.187
3.06
.247
.0053
.0291
.020
1.743
.165
3.05
.220
-.0204
.0402
.049
1.602
.278
3.06
.229
-.0100
.0373
.038
1.645
.237
3.06
.248
-.0012
•0333
.029
1.685
.203
“4.09
•332
.0197
-.0369
“4.09
.345
.0207
-.0389
“4.10
.369
.0234
-.0423
4.08
.315
.0238
.0026
-.003
1.930
....
4.08
.327
.0261
.0024
-.004
1.942
- - -
4.10
.356
.0290
-.0005
-.005
1.949
- - -
4.00
.318
.0134
.0083
.009
1.831
.086
4.08
.328
.0181
.0090
.006
1.867
.065
4.10
.356
.0261
.0023
-.002
1.922
.025
4.08
.320
.0063
.0118
.018
1.776
.137
4.08
.330
.0095
.0130
.016
1.789
.129
4.10
.357
.0158
.0099
.010
1.823
.107
4.00
.323
-.0070
.0179
.034
1.681
.220
4.08
.332
.0005
.0169
.026
1.716
.188
4.10
.360
.0075
•0139
.020
1.745
.165
4.08
.325
-.0189
.0208
.048
1.606
.278
4.08
.334
-.0085
.0194
.038
1.643
.238
4.10
.363
.0017
.0170
.028
1.691
.201
a 5.n
.418
.0222
-.0307
_ _ _
- - -
“5.12
.435
.0235
-.0337
*5.13
.473
.0276
-.0390
—
- - -
5.10
.410
.0259
-.0128
-.003
1.929
- - -
5.11
.426
.0281
-.0123
-.004
1.943
- - -
5.13
.472
.0330
-.0182
-005
1.947
- - -
5.10
.413
.0164
-.0067
.008
1.842
.080
5.11
.429
.0209
-.0081
.006
1.871
.052
5.13
.470
.0300
-.0150
-.003
1.931
.021
5.U
.415
.0096
-.0045
.017
1.783
.129
5-11
.433
.0123
-.0039
.016
1.790
.129
5.13
.471
.0207
-.0085
.009
1.832
.104
5.11
.421
-.0051
.0011
.034
I.685
.224
5.12
.437
.0039
-.0002
.026
1.717
.185
5-13
.476
.0122
-.0044
.019
1.752
.166
5.U
.424
-.0156
.0047
.047
1.617
.274
5-12
.440
-.0050
.0005
.038
1.647
.236
5.13
.477
.0062
-.0017
.026
1.699
.201
a 6.13
.502
.0253
-.0242
- - -
“6.14
.524
.0270
-.0281
- - -
“6.16
• 571
.0366
-.0350
—
6.13
• 502
.0290
-.0269
-.003
1.932
- . -
6.14
.524
.0319
-.0288
-.003
1.944
- - -
6.16
.584
.0411
-.0387
-.005
1.954
- - -
6.13
.508
.0212
-.0226
.006
1.852
.066
6.14
• 529
.0241
-.0243
.006
1.866
.069
6.16
.584
.0387
-.0362
-.003
1.936
.019
6.13
.5 12
.0126
-.0202
.016
1.786
.130
6.14
.533
.0162
-.0210
.016
1.793
.132
6.16
.588
.0294
-.0308
.010
1.832
.106
6.14
.520
-.0013
-.0151
.034
1.685
.221
6.14
• 538
.0076
-.0167
.026
1.717
.189
6.16
• 590
.0210
-.0273
.020
1:756
.165
6.14
.525
-.0120
-.0119
.048
1.612
.276
6.14
.543
-.0009
-.0143
.038
1.646
•239
6.16
.592
.0142
-.0246
.027
1.701
.203
“7.15
• 584
.0291
-.0206
“7.16
.611
.0325
-.0229
_ _ _
- - _
“7.18
.648
.0500
-0299
...
—
7.15
.594
.0336
-.04o4
-.00 3
1.936
_ _ _
7.16
.619
.0373
-.0437
-.004
1.949
- - -
7.19
.678
.0538
-.0471
-.005
1.961
- - -
7.16
• 597
.0257
-.0360
.006
1.862
.067
7.17
.625
.0297
-.0389
.006
1.870
.069
7.19
.684
.0499
-.0474
-.002
1.938
.024
7.16
.603
.0178
-.0343
.016
1.791
.130
7.17
.630
.0221
-.0359
.016
1.796
.133
7.19
.687
.0422
-.0425
.009
1.839
.105
7.16
.613
.0039
-.0296
.034
1.688
.220
7.17
.638
.0132
-.0313
.027
1.716
.193
7.19
.689
.0363
-.0399
.020
1.773
.156
7.16
.620
-.0069
-.0254
.048
1.612
.278
7.17
.644
.0053
-.0289
.038
1.647
.242
7.19
.690
.0298
-.0387
.028
1.708
.200
“8.17
.663
.0346
-.0115
_ _ _
“0.18
.692
.0417
-.0147
- - -
- - _
“8.19
.700
.0679
-.0160
—
—
- - -
8.18
.685
.0396
-.0507
-.003
1.933
- - >
8.19
.715
.0460
-.0556
-.004
1.952
- - -
8.20
.748
.0713
-.0419
-.005
1.967
- - -
8.18
.693
.0317
-.0496
.009
1.838
.087
8.19
.724
.0383
-.0520
.006
1.869
.073
8.20
.750
.0688
-.0409
-.002
1.939
.030
8.19
•699
.0225
-.0471
.020
1.774
.150
8.20
.731
.0317
-.0400
.016
1.800
• 131
8.20
.753
.0620
-.0370
.010
1.844
.106
8.19
.7 n
.0094
-.0435
.036
1.673
.230
8.20
.735
.0233
-.0456
.027
1.720
.192
8.20
• 754
.0539
-.0338
.020
1.767
.162
8.19
.710
.0006
-.04o8
.049
1.611
.278
0.20
.743
.0165
-.0422
.039
1.648
.236
0.21
.758
.0492
-.0325
.027
1.718
.197
“9.19
•735
.0429
-.0011
_ _ _
- - *
“9.19
.750
.0597
-.0103
_ _ _
- - _
“9.19
.7*3
.0862
-.0024
—
9.20
.765
.0474
-.0597
-.003
1.942
- - .
9.21
.002
.0598
-.0629
-.005
1.956
- - -
9.21
.802
.0928
-.0397
-.005
1.973
- - -
9.20
.778
.0387
-.0573
.009
1.849
.085
9.22
.811
.0523
-.0593
.007
1.871
.077
9.22
.806
.0900
-.0374
-.003
1.949
.029
9.21
.786
.0310
-.0541
.020
1.777
.149
9.22
.816
.0456
-.0566
.016
1.799
• 137
9.22
.816
.0848
-.0328
.010
1.845
.114
9.21
•799
.0188
-.0485
.036
1.676
.230
9.22
.823
.0376
-.0538
.027
1.719
.195
9.22
.825
.0753
-.0295
.020
1.767
.168
9.22
.805
.0111
-.0463
.047
1.619
.275
9.22
.026
.0311
-.0522
.038
1.661
.239
9.22
.830
.0700
-.0278
.028
1.716
.203
“10.20
.798
.0589
.0102
_ _ _
...
- - -
“10.21
.806
.0803
-.0007
_ . _
“l0.19
.782
.1091
-.0045
—
10.22
.843
• 0598
-.0674
-.003
1.952
_ _ _
10.22
.858
.0808
-.0662
-.005
1.962
- - -
10.22
.842
.1130
-.0433
-.006
1.984
- - -
10.22
.852
.0505
-.0624
.009
1.853
.089
10.22
.864
.0723
-.0603
.007
1.876
.081
10.22
.855
.1120
-.0378
-.001
1.948
.039
10.22
.861
.0434
-0575
.019
1.785
.152
10.23
.876
.0666
-.0554
.017
1.798
.142
10.23
.868
.1032
-.0396
.011
1.848
.115
10.23
.875
.0310
-.0512
.036
1.684
.235
10.24
.886
.0593
-.0528
.027
1.725
•197
10.23
.868
.0970
-.0422
.020
1.777
.166
10.23
.883
.0242
-.0483
.048
1.623
.278
10.24
.892
.0532
-.0508
.038
1.668
-.239
10.23
.874
.0922
-.0427
.028
1.718
.208
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
TABLE X.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE IRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 1+0° OF SWEEPBACK AND AN ASPECT RATIO OF lOj TAIL OFF, 3 = kl° , R = 2,000,000
M = 0.60, 0.70, 0.80
M, 0.60
M, 0.70
H, 0.80
a .
CL
°x
Cb
T cav
Jav
CPav
a
Cl
Cx
c B
T cav.
Jav.
c Pav
*
cl
cx
Ca
T cav.
Jav
Cp av
*2.04
0.159
0.0174
-0.0429
- - -
...
_ _ _
*2.04
0.161
0.0179
-0.0452
- - .
_ _ _
_ _ _
‘2.04
0.167
0.0207
-0.0478
2.04
.153
.0207
-.0626
-0.003
1.946
- —
2.04
.157
.0218
-.0629
-0.005
1.934
...
2.04
.162
.0246
-.0683
-0.006
1.958
_ _ .
2.04
.152
.0085
-.0550
.009
1.849
0.103
2.04
.156
.0174
-.0598
.001
1.893
0.04l
2.04
.163
•0195
-.0645
.001
1.902
0.046
2.04
• 151
.0036
-.0517
.015
1.807
.139
2.04
.15*
.0056
-.0519
.015
1.787
.132
2.04
.162
.0121
-.0610
.010
1.027
.098
2.04
.150
-.0096
-.0449
.031
1.707
.223
2.04
.154
-.0056
-.0475
.028
1.691
.201
2.04
.161
-.0017
-.0531
.025
1.705
.189
2.04
.149
-.0214
-.0405
.046
1.626
.277
2.04
• 153
-0157
-.0426
.039
I.618
.251
2.04
.161
-.0052
-.0508
.031
1.671
.214
a 3*06
.247
.0182
-.0383
_ _ _
_ _ _
®3.07
•255
.0187
-.0426
- - -
_ _ _
_ _ _
‘3.07
.269
.0211
-.0474
_ _ _
- - -
_ _ _
3.06
.241
.0214
-.0536
-.004
1.943
...
3.06
.250
.0222
-.0548
-.004
1.935
...
3.07
.265
.0252
-.0614
-.006
1.959
3.06
.241
.0112
-.0480
.009
1.845
.084
3.06
.251
.0106
-.0528
0
1.903
.033
3.07
.266
.0202
-0569
0
1.909
.045
3.06
.242
.0039
-.0450
.018
1.786
.137
3.06
.252
.0081
-.0458
.013
1.803
.119
3.07
.267
.0108
-.0512
.012
1.810
.119
3.06
.242
-.0100
-.0375
.035
1.686
.224
3.06
.252
-.0047
-.0382
.028
1.697
.203
3.C7
.268
.0017
-.0466
.023
1.728
.180
3.06
.242
-.0203
-.0330
.048
1.618
.278
3.06
.253
-.0145
-0349
.039
1.621
.252
3.07
.268
-.0033
-.0449
.030
1.687
.209
•4.09
• 332
.0197
-.0369
...
- - -
‘4.09
.345
.0207
-.0389
a 4.l0
• 369
.0234
-.0423
...
4.08
• 329
.0227
-.0442
-.003
1.942
—
4.09
.342
.0240
-.0479
-.004
1.936
- - -
4.10
.369
.0272
-.0522
-.005
1.957
- —
4.08
.331
.0127
-.0383
.010
1.841
.085
4.09
.343
.0211
-.0447
0
1.910
.039
4.10
.369
.0229
-.0481
0
1.913
.042
4.00
• 332
.0070
-.0351
.017
1.794
.127
4.09
.346
.0104
-.0377
.013
1.807
.116
4.10
.371
• 0139
-.0429
.012
1.819
.114
4.08
.334
-.0083
-.0278
.034
1.691
.225
4.09
.348
-.0021
-.0308
.027
1.703
.198
4.10
.374
.0035
-.0367
.024
1.725
.185
4.09
.336
-.0186
-.0234
.048
1.619
.275
4.09
• 350
-.0117
-.0275
.040
1.625
.247
4.10
.376
-.0005
-.0349
.029
1.691
.208
‘5-11
.418
.0222
-.0307
_ _ _
®5.12
.435
.0235
-.0337
‘5.13
.473
.0276
-.0390
...
> - .
5.10
.414
.0249
-.0365
-.003
1.941
...
5.12
.435
.0267
-.0390
-.004
1.932
- _ _
5.U
.474
.0316
-.0466
-.005
1.958
...
5.11
.419
.0154
-.0298
.009
1.843
.083
5.12
.436
.0247
-.0373
-.002
1.920
.021
5.13
.474
.0271
-.0423
0
1.916
.040
5.11
.422
.0095
-.0269
.016
1.797
.125
5.12
.441
.0138
-.0290
.012
1.815
.113
5.13
.479
.0184
-.0364
.012
1.022
.116
5.U
.426
-.0051
-.0192
.034
1.696
.219
5.12
.445
.0027
-.0226
.025
1.715
.188
5.13
.483
.0079
-.0300
.024
1.727
.197
5.H
.429
-.0165
-0139
.047
1.621
.280
5-11
.448
-.0081
-.0181
.037
1.635
.245
5.13
.485
.0036
-.0285
.030
1.684
.209
*6.13
.502
.0253
-.0242
®6.l4
.524
.0270
-.0201
- - -
. _ _
_ _ _
‘6.16
.571
.0366
-.0350
_ . _
6.13
.500
.0280
-.0276
-.003
1.943
—
6.14
• 525
.0305
-.0297
-.004
1.937
- —
6.16
.581
•0391
-.0412
-.005
1.964
6.13
• 505
.0177
-.0210
.011
1.838
.089
6.14
.525
.0285
-.0279
.001
1.925
.018
6.16
.582
.0358
-.0373
-.001
1.927
.033
6.13
.508
.0121
-.0180
.017
1.796
.129
6.14
• 532
.0172
-.0210
.012
1.814
• 113
6.16
• 586
.0258
-.0311
.013
1.017
.122
6.14
• 515
-.0029
-.0096
.035
1.691
.229
6.14
.537
.0057
-.0139
.026
1.718
.186
6.16
.589
.0165
-.0255
.024
1.733
.185
6.14
.518
-.0127
-.0056
.047
1.625
.277
6.14
.542
-.0034
-.0002
.038
1.639
.243
6.16
• 592
.0131
-.0233
.030
1.694
.255
*7-15
.584
.0291
-.0206
®7.l6
.611
.0325
-.0229
...
_ _ _
®7.l8
-.648
.0500
-.0299
_ . _
...
...
7-15
.585
.0323
-.0179
-.003
1.946
...
7.16
.615
.0357
-.0229
-.004
1.940
...
7.18
.674
.0515
-.0325
-.005
1.971
-
7.15
• 589
.0233
-.0121
.009
1.852
.078
7.16
.621
.0281
-.0159
.005
1.866
.072
7.18
.676
.0473
-.0285
0
1.929
.040
7-15
• 592
.0162
-.0080
.017
1.795
.133
7.17
.627
.0174
-.0080
.019
1.765
.161
7.19
.678
.0395
-.0236
.012
1.830
.117
7.16
.601
.0027
-.0004
.034
1.696
.223
7.17
.630
.0123
-.0053
.026
1.720
.190
7.19
.679
.0296
-.0191
.024
1.738
.187
7-16
.607
-.0078
.0050
.047
1.625
.280
7.17
.637
.0023
.0001
.038
1.635
.246
7.19
.681
.0270
-.0170
.030
1.702
.209
•8.17
.663
.0346
-.0115
*8.18
.692
.0417
-.0147
...
‘8.19
.700
.0679
-.0160
...
...
8.17
.665
.0378
-.0072
-.003
1.946
...
8.19
.702
.0441
-.0140
-.005
1.948
...
8.20
.734
.0691
-.0106
-.005
1.975
...
8.17
.674
.0290
-.0011
.009
1.853
.083
8.19
.7 12
.0358
-.0065
.007
1.861
.081
8.20
.737
.0658
-.0069
0
1.932
.039
8.18
.679
.0211
.0033
.018
1.792
.140
8.19
.719
.0270
.0014
.019
1.771
.153
8.20
.737
.0569
-.0026
.012
1.834
.122
8.18
.689
.0087
.0108
.034
1.694
.226
8.19
.723
.0219
.0051
.026
1.718
.193
8.20
.742
.0482
.0030
.024
1.743
.185
8.19
.696
-.0002
•oiyr
.046
1.630
.277
8.19
.726
.0130
.0095
.037
1.651
.245
8.20
.745
.0451
.0062
.030
1.701
.211
*9.19
.735
.0429
-.0011
“9.19
.750
.0597
-.0103
...
_ _ .
“9.19
.743
.0862
-.0024
...
9-19
.741
.0452
.0047
-.003
1.951
- - -
9.20
.779
.0575
-.0003
-.005
1.956
...
9.21
.782
.0900
.0064
-.005
1.979
...
9-19
.753
.0349
.0126
.010
1.849
.096
9.21
.787
.0509
-.0039
.005
1.878
.065
9.21
.793
.0867
.0123
-.001
1.939
.050
9.20
.758
.0280
.0169
.019
1.788
.151
9.21
.757
.0404
.0126
.019
1.775
.158
9.21
.798
.0786
.0184
.011
1.841
.119
9.20
.770
.0171
.0243
.034
1.697
.227
9.21
.800
.0354
.0152
.026
1.724
.194
9.21
.808
.0704
.0245
.023
1.752
.184
9.20
.777
.0088
.0291
.047
1.630
.278
9.21
.805
.0281
.0192
.037
1.650
.246
9.22
.dll
.0655
.0265
.030
1.706
.217
‘10.20
.798
.0589
.0102
- - -
‘10.21
.806
.0003
-.0007
...
...
‘10.19
.782
.1091
-.0045
...
...
...
10.21
.814
•0569
.0209
-.004
1.963
...
10.21
.828
.0784
.0191
-.005
1.960
...
10.21
.823
.1121
.0239
-.006
1.989
10.21
.823
.0472
.0278
.010
1.056
.095
10.22
.843
.0715
.0251
.006
1.877
.079
10.21
.832
.1086
.0299
-.001
1.946
.039
10.21
.831
.0402
.0316
.019
1.795
.151
10.22
.852
.0623
.0296
.019
1.781
.159
10.22
.841
.0986
.0298
.011
1.840
.126
10.22
.844
.0290
.0386
.034
1.702
.232
10.22
.861
.0558
.0325
.028
1.721
.202
10.22
.846
.0935
.0302
.022
1.762
.183
10.22
.850
.0217
.0423
.046
1.642
.278
10.23
.864
.0506
.0362
.037
1.664
.243
10.22
.849
.0908
.0313
.028
1.716
.211
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
TABLE XI.- LONGITUDINAL CHARACTERISTICS OF A FOUR -ENGINE TRACTOR AIRPLANE CONFIGURATION HAVING
A WING WITH 40° OF SWEEPBACK AND AN ASPECT RATIO OF 10; TAIL HEIGHT = 0.10 b/2, l t = -4°,
CO
3 = 51°, R = 1,000,000
M = 0.70, 0.80, 0.90
M, 0.80
a
CL
cx
c «
T Cav
J.v
C Pav
a
c L
Cx
Cb
Tc av
*7av
c Pav
a
Cl
cx
Cm
T C av
Jav
*2.03
0.122
0.0228
0.0994
*2.03
0.129
0.0252
0.0995
*2.03
0.143
0.0407
0.1135
2.02
• 113
.0247
.0729
-0.003
2.777
. _ -
2.03
.122
.0282
.0690
-0.004
2.743
- - -
2.04
.154
.0439
.0557
-0.005
2.719
2.02
.109
.0155
.0788
.008
2.575
0.207
2.03
.118
.0193
.0783
.006
2.554
0.187
2.04
.151
.0334
.0673
.009
2.521
2.02
.106
.0059
.0873
.021
2.370
.363
2.03
.1 16
.0096
.0885
.018
2.354
.353
2.04
.148
.0236
.0818
.016
2.270
2.02
.103
-.0077
.0996
.037
2.173
.539
2.03
• 115
-.0015
.1002
.032
2.163
.490
2.04
.146
.0141
.0935
.028
2.030
2.02
.102
-.0237
.1091
.057
1.959
.713
2.02
.113
-.0138
.1075
.047
1.974
• 592
2.04
.145
.0077
.0988
•035
1.894
a 3.06
.226
.0231
.0697
*3.06
.244
.0253
.0640
- - -
. _ _
*3.06
.242
.0443
.0776
3-05
.217
.0251
.0495
-.002
2.781
_ _ _
3.06
.238
.0282
.0436
-.004
2.745
- - -
3-07
.260
.0492
.0224
-.005
2.732
3.05
.214
.0157
.0564
.008
2.569
.199
3.06
.234
.0197
.0541
.006
2.559
.183
3.07
.263
.0399
.0355
.005
2.533
3.05
.213
.0054
.0648
.021
2.377
.381
3.06
.234
.0095
.0642
.018
2.358
.359
3.07
.267
.0281
.0477
.019
2.245
3.05
.213
-.0074
.0779
.036
2.175
.539
3.06
.235
-.0013
.0757
.032
2.165
.491
3.07
.268
.0185
.0540
.027
2.071
3.05
.212
-.0234
.0877
.057
1.962
.659
3.06
.235
-.0127
.0833
.046
1.992
.585
3-07
.272
.0122
.0610
.034
1.913
B 4.o8
.326
.0244
.0427
_ _ _
_ _ _
a 4.10
.355
.0281
.0417
...
. _ _
*4.08
.330
.0535
.0508
—
4.08
.322
.0266
.0277
-.002
2.778
4.09
• 351
.0303
.0260
-.004
2.744
—
4.09
• 354
.0583
.0082
-.005
2.728
4.08
.318
.0181
.0349
.008
2.576
.186
4.09
.349
.0218
.0370
.006
2.565
.191
4.09
.351
.0521
.0219
.002
2.591
4.08
.318
.0068
.0459
.021
2.376
.380
4.09
.350
.0123
.0473
.018
2.367
.352
4.10
.358
.0407
.0305
.013
2.345
4.08
• 320
-.0061
.0593
.037
2.180
.543
4.09
.353
.0014
.0584
.032
2.172
.488
4.10
.362
.0312
.0376
.023
2.143
4.08
.321
-.0281
.0714
.056
1.964
.663
4.09
.354
-.0105
.0672
.046
1.995
• 595
4.10
.370
.0226
.0454
•033
1.937
a 5.11
.424
.0269
.0216
_ _ _
*5-13
.466
.0331
.0218
*5.10
.417
.0653
.0357
5.11
.420
.0289
.0145
-.002
2.772
_ _ _
5-12
.463
.0350
.0110
-.004
2.752
- - -
5.11
.434
.0692
.0058
-.005
2.743
5.11
.418
.0202
.0220
.007
2.575
.184
5-12
.464
.0270
.0226
.007
2.568
.179
5.12
.438
.0609
.0159
j004
2.562
5.H
.421
.0089
.0343
.021
2.377
.388
5.13
.465
.0167
.0343
.019
2.371
.356
5 .12
.445
.0516
.0254
.014
2.353
5.H
.424
-.0036
.0501
.038
2.177
.545
5.13
.468
.0058
.0468
.033
2.173
.497
5.12
.443
.0455
.0338
.024
2.148
5.11
.427
-.0169
.0606
•055
1.969
.665
5.13
.471
-.0046
.0538
.046
2.006
• 592
5.12
.448
.0380
.0390
•033
1.960
a 6.l4
• 523
.0309
.0013
*6.15
.563
.0440
.0006
*6.13
.493
.0799
.0325
6.14
.519
.0327
-.0019
-.002
2.784
...
6.16
.567
.0431
-.0047
-.004
2.756
—
6.13
.512
.0822
.0068
-.004
2.757
6.14
• 519
.0265
.0078
.008
2.575
.186
6.16
.570
.0353
.0091
.007
2.571
.186
6.14
.517
.0743
.0179
.005
2.562
6.14
.522
.0137
.0210
.022
2.383
.385
6.16
• 573
.0265
.0218
.019
2.377
.350
6.14
.517
.0699
.0229
.014
2.370
6.14
• 526
.0014
.0347
.039
2.181
.548
6.16
.577
.0165
.0337
•033
2.183
.494
6.14
• 532
.0586
.0303
.023
2.174
6.14
.533
-.0126
.0448
.057
1.966
.657
6.16
.580
.0061
.0406
.047
2.011
.590
6.14
.540
.0511
.0354
.033
1.974
*7.16
.616
.0371
-.0187
- - -
_ _ _
*7.14
.635
.0593
-.0064
*7.14
.559
.0940
.0305
7.16
.614
.0386
-.0184
-.001
2.785
_ _ _
7.18
.662
.0575
-.0123
-.004
2.767
- - -
7.15
.592
.0984
.0035
-.004
2.766
7.16
.616
.0304
-.0086
.009
2.575
.197
7.18
.665
.0492
-.0026
.007
2.579
.188
7.15
.594
.0907
.0142
.006
2.554
7.16
.621
.0205
.0031
.023
2.384
.387
7.18
.668
.0407
.0107
.019
2.379
.359
7.16
.596
.0852
.0194
.014
2.377
7.17
.627
.0089
.0165
.038
2.184
.548
7.18
.669
.0309
.0209
•033
2.183
.505
7.16
.600
.0807
.0225
.023
2.194
7.17
.635
-.0033
.0253
.056
1.992
.665
7.18
.671
.0211
.0262
.047
2.011
.595
7.16
.613
.0742
.0277
•032
1.997
a 8.19
.701
.0490
-.0318
- _ -
*8.18
.688
.0779
-.0009
*8.16
.627
.1132
.0266
8.19
.706
.0481
-.0285
-.001
2.789
- - -
8.19
.722
.0756
-.0036
-•005
2.782
- - -
8.17
.651
.1193
.0096
-.005
2.780
8.19
.711
.0404
-.0189
.008
2.589
.200
8.20
.728
.0672
.0064
.007
2.583
.198
8.17
.667
.1130
.0118
.003
2.617
8.19
.716
.0312
-.0093
.023
2.386
.392
6.20
.735
.0593
.0158
.018
2.389
.3 60
8.17
.674
.1057
.0154
.013
2.415
8.19
•723
.0198
.0022
.038
2.185
.554
8.20
.739
.0496
.0242
.033
2.190
.505
8.18
.680
.0985
.0195
.022
2.216
8.20
.730
.0087
.0114
.057
1.980
.660
8.20
.743
.0406
.0280
.046
2.025
.597
8.18
.683
.0936
.0184
.032
2.008
*9.20
.759
.0685
-.0378
...
_ _ _
*9.19
.729
.0986
-.0021
_ _ _
...
*9.17
.689
.1346
.0214
9.20
.781
.0642
-.0301
0.
2.804
...
9.20
.772
.0963
.0032
-.005
2.786
- - -
9.18
.716
.1401
.0126
-.005
2.795
9.21
.787
.0549
-.0251
.010
2.586
.227
9.21
.787
.0882
.0094
.005
2.600
.189
9.19
.734
.1352
.0065
.003
2.626
9.21
.796
.0472
-.0189
.023
2.391
.393
9.21
.799
.0798
.0161
.018
2.390
.365
9-19
.742
.1300
.0090
.013
2.430
9.21
.806
.0351
-.0083
.040
2.175
.552
9.21
.802
.0704
.0183
•033
2.188
.518
9.19
.754
.1209
.0124
.022
2.233
9.22
.815
.0257
-.0008
.058
1.991
.658
9.21
.804
.0629
.0198
.046
2.027
.602
9.20
•755
.1158
.0152
.032
2. on
a 10.21
.810
.0918
-.0298
...
- _ -
_ _ .
*10.19
.772
.1211
-.0052
. _ _
*10.18
.749
.1572
.0080
10.22
.846
.0882
-.0223
-.001
2.816
_ _ _
10.21
.815
.1191
.0149
-.006
2.799
- - -
10.19
.780
.1618
.0077
-.005
2.799
10.22
.847
.0796
-0193
.009
2.580
.240
10.21
.823
.1123
.0147
.005
2.599
.205
10.21
.811
.1599
-.0008
.003
2.623
10.22
.860
.0689
-.0132
.022
2.379
.416
10.22
.842
.1037
.0161
.018
2.395
.378
10.21
.817
.1528
.0019
.012
2.433
10.23
.872
.0586
-.0084
.040
2.161
.575
10.22
.855
.0957
.0223
•032
2.200
.518
10.21
.827
.1476
-.0006
.022
2.236
10.23
.882
.0496
-.0002
.056
1.999
.666
10.22
.860
.0879
.0174
.045
2.042
.601
10.18
.832
.1436
.0025
.032
2.036
0.171
.329
.425
.462
*Prope off.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
t
1
> t
(a) Dimensions.
Figure 1.- Geometry of the model.
OU
VO
NACA RM A53J23 CONFIDENTIAL
J4
£r
O
(b) Wing twist and thickness -chord ratio.
Figure 1.- Continued.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
O
> i
All dimensions are in inches unless otherwise noted.
Nacelle coordinates
Sta
n
Sta
r P
-5.00
o
2.00
0.350
-4.79
.385
3.00
.4/9
-4.58
.567
4.00
.6/6
-4.25
.788
5.00
. 9/9
-3.95
.951
6.00
1.290
-325
i .242
7.00
i .685
-2.55
i .472
8.00
2.056
- 1.80
i .670
9.00
2.359
- .80
1.871
/ 0.00
2.556
0
i .985
a. oo
2.625
2.00
2.100
30.50
2.625
12.00
2.100
32.50
2.450
34.50
2.220
36.50
i .825
38.50
i .270
40.50
.675
41.50
.275
42.25
0
Sta 36.00
(c) Nacelle details.
Figure 1.- Continued.
_
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
r\}
Type and location
Small at -£ = 0.33
b /2
Extended at rf - 0.50, 0.70, and 0.85
(d) Fence details.
Figure 1.- Concluded.
)
CONFIDENTIAL NACA RM A53J23
NACA RM A53J23
CONFIDENTIAL
^3
A-17524
Figure 2.- Photograph of the model in the wind tunnel.
CONFIDENTIAL
CONFIDENTIAL
NACA RM A53J23
Figure 3*- Plan-form and "blade-form curves for the NACA l.l67-(0) (03) -058
propeller.
CONFIDENTIAL
Blade-section angle , j3\ deg
CONFIDENTIAL
(a) R = 1 x 10®
Figure 4.- The variation of thrust coefficient with advance ratio for the NACA l.l67-(0) (03) -058
propeller. A = 0°.
•p-
ui
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
4=r
(b) R = 2 X 10 s
Figure 4. - Concluded.
CONFIDENTIAL NACA RM A53J23
O .Oi .02 .03 .04 .05 .06 .07
Thrust coefficient, T c
Figure 5«- Typical variations of lift coefficient with thrust coefficient for assumed full-scale
power conditions. Altitude = 40,000 ft, Tl assumed = O. 65 , W/S = 75 Ib/sq ft.
L
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
£
Propellers Operating
— o- Propellers Off
Longitudinal force coefficient, C x
(a) M = 0.70
Figure 6.- The effect of operating propellers on the longitudinal characteristics of the model.
Tail height = 0 b/2, it = -2°, (3 = 51°, R = 1 X 10 s .
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
-3
n
Propellers Operating
Longitudinal force coefficient, C x
(b) M = 0.80
Figure 6.- Continued.
■p-
VO
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
VJl
o
Propellers Operating
-.02 0 .02 .04 .06 .08 JO .12 .14
Longitudinal force coefficient, C x
(c) M = 0.83
Figure 6.- Continued.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
Propellers Operating
Longitudinal force coefficient, C x
(d) M = 0.86
Figure 6.- Continued.
VJ1
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
to
Propellers Operating
Angle of attack, a, deg Pitching-moment coefficient, Cm
O .02 .04 .06 .08 .10 J2 .14 .16
Longitudinal force coefficient, C x
(e) M = 0.90
Figure 6.- Concluded.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
Propellers Operating
Longitudinal force coefficient, C x
(a) M = 0.70
Figure 7.- The effect of operating propellers on the longitudinal characteristics of the model.
Tail height = 0 b/2, i t = -k°, 3 = 51°, R = 1 x 10 6 . v*
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
VJ1
-r
Propellers Operating
— o — Propellers Off
Longitudinal force coefficient, C x
(b) M = 0.80
Figure 7» - Continued.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
Propellers Operating
Longitudinal force coefficient, C x
(c) M = 0.83
Figure 7-- Continued.
L
vji
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
vn
0 \
Propellers Operating
—o— Propellers Off
-.02 O 02 04 06 08 .10 .12 .14 .16
Longitudinal force coefficient, C x
(d) M = 0.86
Figure 7* - Continued.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
CD
O
■Propellers Operating
Longitudinal force coefficient, C x
(e) M = 0.90
Figure 1.- Concluded.
v_n
-o
L
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
VJ1
03
Propellers Operating
— o — Propellers Off
Longitudinal force coefficient, C x
(a) M = 0-70
Figure 8.- The effect of operating propellers on the longitudinal characteristics of the model.
Tail height = 0 b/2, i t = -6°, p = 51°, R = 1 X 10 6 .
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
Propellers Operating
Longitudinal force coefficient, C x
(b) M = 0.80
Figure 8.- Continued.
ui
M3
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
ON
o
- Propellers Operating
-Propellers Off
Longitudinal force coefficient, C x
I
(c) M = 0.83
Figure 8.- Continued.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
Propellers Operating
— o- Propellers Off
Longitudinal force coefficient, C x
(a) m = 0.86
Figure 8.- Continued
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
CT\
ro
Propellers Operating
— o- Propellers Off
Longitudinal force coefficient, C x
(e) M = 0.90
Figure 8.- Concluded.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
*
Propellers Operating
(a) M = 0.70
Figure 9« - Hie effect of operating propellers on the longitudinal characteristics of the model.
Tail off, 0 = 51°, R = 1 X 10 s .
CT\
UO
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
O'
■F
Propellers Operating
— o— Propellers Off
-.02 0 .02 04 .06 .08 .iO .12
Longitudinal force coefficient, C x
(b) M = 0.80
Figure 9.- Continued.
CONFIDENTIAL NACA RM A53J23
CO
O
o
o
H
tH
Propellers Operating
(c) M = 0.83
Figure 9 .- Continued,
o
\j\
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
(T\
( 7 >
Propellers Operating
Propellers Off
-02 O .02 .04 .06 .08 JO .12 .14
Longitudinal force coefficient, C x
\
(d) M = 0.86
Figure 9*~ Continued.
I
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
* * It »
Propellers Operating
Longitudinal force coefficient, C x
(e) M = 0.90
3
Figure Concluded.
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
ON
CP
Propellers Operating
} w i- ■■ ■ i . .. w i . i w 1 — i -i — i, T . i , i ■■ i —
O 4 8 12 .16 .12 .08 .04 0 -.04 -.08
Angle of attack, a, deg Pitching-moment coefficient, Cm
-.02 O .02 .04 .06 .08 ./O
Longitudinal force coefficient, C x
(a) M = 0.70
Figure 10.- The effect of operating propellers on the longitudinal characteristics of the model.
Tail height = 0.10 b/2, i t = - 4 °, p = 51°, R = 1 x 10 6 .
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
Propellers Operating
Longitudinal force coefficient, C x
Cb) M = 0.80
Figure 10.- Continued.
ON
ND
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
-4
o
■Propellers Operating
Longitudinal force coefficient, C x
(c) M = 0.90
Figure 10.- Concluded.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
» •
Propellers Operating
(a) M = O.TO
Figure 11.- The effect of operating propellers on the longitudinal characteristics of the model
Tail height = 0 b/2, i t = -4°, p = 51°, E = 2 x 10 6 .
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
-j
ro
Propellers Operating
O 4 8 12 .08 .04 0 - 04 -.08 -.12
Angle of attack, a , deg Pitching-moment coefficient. Cm
0 .02 .04 .06 .08 .10 .12
Longitudinal force coefficient, C K
(b) M = 0.80
Figure 11.- Continued.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
o
O
■Propellers Operating
Longitudinal force coefficient, C x
(c) M = 0.90
Figure 11.- Concluded.
-j
uu
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
-J
-p-
Propellers Operating
Angle of attack, a, deg Pitching-moment coefficient, Cm
O .02 .04 .06 .08 JO
Longitudinal force coefficient, C x
(a) M = O.TO
Figure 12.- The effect of operating propellers on the longitudinal characteristics of the model.
Tail off, 3 = 51°, R = 2 X 10 6 .
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
Propellers Operating
Propellers Off
0 .02 .04 .06 .08 JO .12
Longitudinal force coefficient, C x
(b) M = 0.80
Figure 12.- Continued.
VJ1
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
O'
Propellers Operating
Longitudinal force coefficient, C x
(c) M = 0.90
Figure 12.- Concluded.
CONFIDENTIAL NACA EM A53J23
CONFIDENTIAL
Propellers Operating
—o— Propellers Off
Longitudinal force coefficient, C x
(a) M = 0.60
Figure 13. - The effect of operating propellers on the longitudinal characteristics of the model.
Tail height = 0 fc/2, it = -4°, 3 = 4l°, R = 2 X 10 s .
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
03
Propellers Operating
-o— Propellers Off
Longitudinal force coefficient, C x
Ob) M = 0.70
Figure 13*- Continued.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
Propellers Operating
-A
MD
Figure 13 .- Concluded.
MCA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
8
■Propellers Operating
■ Propellers Off
0 4 8 12 04 0 -.04 -.08
Angle of attack, a, deg Pitching-moment coefficient, Cm
-.02 0 .02 .04 .06 ^£ 55 ^
Longitudinal force coefficient, C x
(a) M = 0.60
Figure l4. - The effect of operating propellers on the longitudinal characteristics of the model.
Tail off, p = l+l 0 , R = 2 x 10 6 .
COOTIDENTIAL NACA RM A53J23
CONFIDENTIAL
■Propellers Operating
Ob) M = 0.70
Figure l4.- Continued.
cn
t— 1
lie NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
CD
ro
0 4 8 12 .04 0 -.04 -.08
Angle of attack, a, deg Pitching-moment coefficient, Cm
-.02 0 .02 .04 .06 .08 .10 .12
Longitudinal force coefficient, C x
(c) M = 0.80
Figure 1^.- Concluded.
CONFIDENTIAL NACA RM A53J23
Lift- curve slope
NACA RM A53J23
CONFIDENTIAL
83
(a) Tail height = 0 b/2, i-t = -4°.
Figure 15.- The effect of Mach number at constant lift coefficient on
the lift-curve slopes of the model with and without operating pro-
pellers. 0 = 51 °, R = 1 x 10 s .
CONFIDENTIAL
CONFIDENTIAL
NACA RM A53J23
Mach number, M
(b) Tail off.
Figure 15.- Concluded.
CONFIDENTIAL
Longitudinal force coefficient increment ,
NACA RM A53J23
CONFIDENTIAL
85
Figure 1 6 .- The effect of Mach number at constant lift coefficient on
the longitudinal force coefficient increment of the model with and
without operating propellers. Tail height = 0 b/2, i-fc = -4°, p = 51°,
R = 1 X 10 6 .
CONFIDENTIAL
Pitching -moment-curve slope , -rfP
86
CONFIDENTIAL
NACA RM A53J23
7 .8 .9
Mach number , M
(a) Tail height » 0 b/2, it = -V 3 .
Figure 17*- The effect of Mach number at constant lift coefficient on
the pitching-moment-curve slopes of the model with and without oper-
ating propellers, p = 51°, R = 1 x 10 s .
CONFIDENTIAL
Pitching- moment -curve slope —
' * ///'
NACA RM A53J23
CONFIDENTIAL
87
(b) Tail off.
Figure 17. - Concluded.
CONFIDENTIAL
CONFIDENTIAL
O.
s
ts
V.
Q
m props off
props off* ^^ m prop thrust
C ^ ^
m props off m prop thrust m prop normal force
Pitching -moment coefficient , C m
(a) M = 0.70
Figure 18.- The various effects of operating propellers at constant thrust on the pitching-
moment characteristics of the model. Tail height = 0 b/2, it = -4°, p = 51°, R = 1 x 10 s .
00
CD
*
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
(S3
O
Cm.
n props off
C- .. +AC„
m props off m prop thrust
'props off + A Cm p^p thrust
Cm„
Mprops off m prop thrust m prop normal force
7 ! 'props off ^ ^m prop thrust + prop normal force
Mprops on
c*
*»c
J5
o
A
£
10
8
^ i
. V
\
y
//
\
\
\
\ '
\
II
j
A
r~
\
m\
ii
\\
!(
r y
1
N
“A\
\ \\
s\v
\ \
\ >
VV/
1
/
\
ij
T c .O.Ot
/!
/ /
/
/
✓ ,
/ /,
t/
\ ■
\
\
/
/
✓
W
\
i\
✓
✓
V
'It
\i i
\i i
Tail on
Tail off
'^NACA,^'
—
.08 .04 0 -.04 -.08 -.12
Pitching -moment coefficient,
(b) M = 0.80
Figure l8.- Continued
oo
MO
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
8
o
£
m props off
CL +AC m
m props off prop thrust
Cm -/■ ^ CL ~t~ 4 CL
m props off m prop thrust m prop normal force
Pitching -moment coefficient, C m
t
(c) M = 0.90
Figure 18.- Concluded.
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
*
r
m props off
Cm props off~ i ~ ACm prop thrust
m props off prop thrust + AC ">prop normal force
m props off +AC ™ P rop thrust + AC ™ prop normal force + AC ™prop slipstream ' Mprops on
(a) 2500 hp per engine.
Figure 19.- The various effects of operating propellers at constant simulated horsepower on the
pitching -moment characteristics of the model. Tail height = 0 h/2, i+ = -k° r = 51°
R = 1 x 10°. u w J >
VO
NACA RM A53J23 CONFIDENTIAL
CONFIDENTIAL
Q
m props off
ft
■7J7
1 props off ^^rn r
C.
. . ’ prop thrust
7 + id^T -h AC
' m props off m prop thrust m prop normal force
-+ AC,
(t>) 5000 hp per engine.
Figure 19.- Concluded.
4 *
CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
t
Angle
of attack , a, deg
Figure 20.- Comparison of the measured and predicted effects of propeller normal force on incre-
ment of pitching moment and the measured effects of propeller thrust and slipstream on incre-
ment of pitching moment. M = 0.80, T c = O.Oh, tail height = 0 b/2. i+ = -4°, 0 = 51°,
■D — T vx 1 A 6 0 7 7
VO
LaJ
NACA RM A53J23 CONFIDENTIAL
94
CONFIDENTIAL
NACA RM A53J23
Total change in stability parameter due to props
Stability increment due to prop, thrust
Stability increment due to prop, normal force
Stability increment due to prop, slipstream on wing
Stability increment due to prop, slipstream on tail
L
—
1 — ’
Constant power , 2500 hp per engine
.7 .8 .9
Mach number , M
Figure 21.- The variation with Mach number of the various effects of
operating propellers on increment of pitching -moment- curve slope.
C L = 0.1*0, tail height = 0 b/2, i t = -4°, 0 = 51°, R = 1 X 10 6 .
CONFIDENTIAL
Effective downwash angle
NACA RM A53J23
CONFIDENTIAL
95
N
o 2 4 6 8 10 12
O 2 4 6 8 10 12
Angle of attack, a, deg
Figure 22.- The effect of operating propellers on the variation of down-
wash angle with angle of attack. Tail height = 0 b /2, (3 = 51°,
R = 1 X 10 s .
CONFIDENTIAL
96
CONFIDENTIAL
NACA RM A53J23
O 2 4 6 8 10 12
M =
0.70
V
Props off
\
j
rT c
= 0
4
7 — .02
^
—
L
.04
1^1
0 2 4 6 8 10 12
Angle of attack, a , deg
Figure 23.- The effect of operating propellers on the variation of tail-
efficiency factor with angle of attack. Tail height = 0 h/2,
p = 51°, R = 1 X 10 6 .
CONFIDENTIAL
13C
NACA RM A53J23
CONFIDENTIAL
97
Angle of attack, a, deg
Figure 2k. - The effect of operating propellers on the variation with
angle of attack of the ratio of isolated horizontal tail lift-curve
slope to tail-off lift-curve slope. 3 = 51°> R = 1 X 10 6 .
CONFIDENTIAL
98
CONFIDENTIAL
NACA RM A53J23
Mach number , M
Figure 25. - The effect of Mach number on the lift-curve slope of the
isolated horizontal tail. 0^=4°, R=2x 10 s .
. uo
0/1
r T c =0.04, ^ — .02
/
\
-Props off
VT
dC m
* — ___
u
—
d'f
02
n
'c w
\NAC
7 .8 .9
Mach number , M
Figure 26,- The effect of Mach number on the effectiveness of the hori-
zontal tail with and without operating propellers, a = tail
height = 0 b/2, 3 = 51°, R = 1 x 10 6 .
CONFIDENTIAL
NACA RM A53J23
CONFIDENTIAL
99
.7 .8 .9
.7 .8 .9
Mach number. M
Figure 27.- The variation vith Mach number with and without operating
propellers of the factors affecting the stability contribution of the
horizontal tail, a = k°, tail height = 0 b/2, (3 = 51°, R = 1 X 10 6 .
CONFIDENTIAL
100
CONFIDENTIAL
NACA RM A53J23
Tail
height
Props
on
Props
off
o
o./of
—
□
t
M =0.90
,
□
>
<J>
w
O .01 .02 .03 .04 .05 .06
-./
-.3
M =0.70
■ —
—
><
LI
.01 .02 .03 .04
Thrust coefficient, T c
.05
.06
Figure 28.- The effect of hori zontal -tail height on the pitching-moment-
curve slopes of the model with and without operating propellers.
Cl « O.ltO, i t = -4°, p = 51°, R = 1 X 10 6 .
CONFIDENTIAL
NACA RM A53J23
CONFIDENTIAL
101
Propulsive- system characteristics (average, two units)
Isolated- propeller characteristics
.7 .8 .9
Mach number , M
Figure 29 .- Comparison of propulsive characteristics with isolated pro-
peller characteristics. A = 0°, 3 = 51°> R * lx 10 6 .
CONFIDENTIAL
Propeller or propulsive efficiency
CONFIDENTIAL
0
-2
'/
-4
-6
O
dC m -/
dC L
-.2
-.3
.6
.4
.2
O
Power for level flight-
/
/
m *
rr
■ ’
IV
-Props off
C L
.8
.9
- Power for level flight
i
\
s
S. \
Props off
O / 2
Normal acceleration factor . n
12000
8000
6000
hPreq'd.
( P e f i 4000
( eng/ne'
2000
LW-
.7
.8
Mach number t M
Figure 30.- S umm ary of the aerodynamic characteristics of a hypothetical four -engine airplane in
level flight at 1(0,000 feet. Tail height = 0 b/2, T ) assumed = 0.65, w/S = 65 lb/sq ft.
r
102 CONFIDENTIAL NACA RM A53J23
CONFIDENTIAL
R = IxlO 6 , J3 * 5/°
R * 2x!0 6 , fi = 51°
R - 2x!0 e , /3 - 41°
o- Propellers off, R = IxlO 6
□ — Propellers off , R * 2x/0 6
M s 0.70
Thrust
0 02 .04
coefficient, Tc
M - 0.90
(a) Lift-curve and pitching -moment -curve slopes.
Figure 31 • - The variation of the longitudinal characteristics of the model with thrust coeffi-
cient for two propeller blade angles and Reynolds numbers with and without operating pro-
pellers. C L = 0.1+0, tail height = 0 b/2, it - -4°.
o
ou
NACA RM A53J23 CONFIDENTIAL
Longitudinal force coefficient
104
CONFIDENTIAL
NACA RM A53J23
R = IxlO 6 , /3 = 5I° O - Propellers off, R - ixJO 6
R = 2x!0 6 , f9 =51° □ - Propellers off, R = 2x!0 6
R = 2x!0 6 ,/3 =41°
(b) Longitudinal force.
Figure 31.- Concluded.
CONFIDENTIAL
Normal - force coefficient
14C
NACA RM A53J23
CONFIDENTIAL
105
.07
.06
.05
.04
$ .03
.02
. 0 !
0
-. 0 /
-.02
-.03
-.04
-6-4-2 O 2 4 6 8 for M s . 70
Upfiow angle. A, deg
Figure 32.- Normal -force characteristics of the NACA l.l67-(0) (03)-058
propeller. J3 = 51°, R = 1 X 10 6 .
CONFIDENTIAL
NACA-Langley - 1 - 7-54 - 325
O
O
a
Figure 33*- Comparison of measured and predicted normal-force-curve slopes for the
NACA l.l67-(0)(03)-058 propeller. M = 0.80, (3 = 51°, R = 1 X 10 6 .
t
106 CONFIDENTIAL NACA RM A53J23
L
t
I
CONFIDENTIAL
CONFIDENTIAL
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